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@AIRBUSA380
AIRCRAFT CHARACTERISTICSAIRPORT AND MAINTENANCE PLANNING
AC
The content of this document is the property of Airbus.It is supplied in confidence and commercial security on its contents must be maintained.It must not be used for any purpose other than that for which it is supplied, nor mayinformation contained in it be disclosed to unauthorized persons.It must not be reproduced in whole or in part without permission in writing from the owners ofthe copyright. Requests for reproduction of any data in this document and the media authorizedfor it must be addressed to Airbus.
FIGURE Ground Service Connections -VFG Oil Servicing - GP 7200 Engines
R ILLUSTRATION REVISED
Starter Oil Servicing R
HIGHLIGHTSPage 13
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
LOCATIONS CHGCODE
DESCRIPTIONS OF CHANGE
FIGURE Ground Service Connections -Starter Oil Servicing - TRENT 900Engines
R ILLUSTRATION REVISED
FIGURE Ground Service Connections -Starter Oil Servicing - GP 7200 Engines
R ILLUSTRATION REVISED
APU Oil Servicing R
FIGURE Ground Service Connections -APU Oil Servicing
R ILLUSTRATION REVISED
Subject 05-04-10 R
Vacuum Toilet System R
FIGURE Ground Service Connections -Vacuum Toilet System
R ILLUSTRATION REVISED
FIGURE Ground Service Connections -Waste Tanks Location
R ILLUSTRATION REVISED
Section 05-05 R
Subject 05-05-00 R
Engine Starting Pneumatic Requirements R DELETED ”AIA/NAS 3601 STANDARD”FROM THE TEXT.
FIGURE Example for Use of the Charts R CORRECTED THE ASU DISCHARGETEMPERATURE 240˚C (464˚F) TO 265˚C(509˚F), FOR INTERPOLATION.REPLACED THE TERM ”OAT” WITH”ASU DISCHARGE TEMPERATURE”.ADDED LEGEND FOR ASU DISCHARGETEMPERATURE CURVES.REPLACED THE TERM ”HPGC” WITH”A/C CONNECTION”, IN THE EXAMPLEFOR REQUIRED AIRFLOW.ILLUSTRATION REVISED
FIGURE Engine Starting PneumaticRequirements - Engine Alliance - GP 7200
R REPLACED THE TERM ”OAT” WITH”ASU DISCHARGE TEMPERATURE”.ADDED LEGEND FOR ASU DISCHARGETEMPERATURE CURVES.ILLUSTRATION REVISED
HIGHLIGHTSPage 14
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
R REPLACED THE TERM ”OAT” WITH”ASU DISCHARGE TEMPERATURE”.ADDED LEGEND FOR ASU DISCHARGETEMPERATURE CURVES.ILLUSTRATION REVISED
Section 05-06 R
Subject 05-06-00 R
Ground Pneumatic Power Requirements R ADDED GROUND PNEUMATIC POWERREQUIREMENTS FOR HEATING ORCOOLING THE CABIN. ADDED NOTESABOUT COOLING CAPACITY AND MAXAIRFLOW.NOTE AMENDED
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
10 AIRCRAFT RESCUE AND FIRE FIGHTING
10-00-00 AIRCRAFT RESCUE AND FIRE FIGHTING
T.O.C.Page 4
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
SCOPE
01-01-00 Purpose
**ON A/C A380-800
Purpose
1. GeneralThe A380 AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING (AC)manual is issued for the A380 series aircraft to provide necessary data to airport operators, airlinesand Maintenance/Repair Organizations (MRO) for airport and maintenance facilities planning.
This revision is now a merging of the Maintenance Facility Planning (MFP) document and theAirplane Characteristics for Airport Planning (AC). This document has been renamed AircraftCharacteristics - Airport and Maintenance Planning (AC) to reflect this change.Additionally, a chapter 10 ”Aircraft Rescue and Fire Fighting” has been added to the AC. Thischapter contains the illustrations of the Aircraft Rescue and Fire fighting Charts poster and replacesthe PDF document that was available for download.
This document is not customized and must not be used for training purposes.
The A380-800 is a subsonic, very long range and very high capacity civil transport aircraft. TheA380-800 offers several payload capabilities ranging from 400 passengers in a very comfortable multi-class configuration, up to 853 passengers in an all economy class configuration.
Designed in close collaboration with major airlines, airports and airworthiness authorities, the A380 isthe most advanced, spacious and productive aircraft in service setting a new standard in air traveland environmental efficiency.
The A380 Family starts from a baseline passenger aircraft - the A380-800. A higher capacity version,the A380-900 could be developed when required by the market.
Two engine types are currently offered, the Engine Alliance GP7200 series and the Rolls-Royce Trent900 series. Both engines use state of the art technology for better performance, maintainability, lowerfuel consumption and environmental impact.
The A380-800 was designed to be compatible with current airport infrastructure and equipment, asproven in service. Bigger, quieter and capable of achieving quick turn around times, the A380-800provides an efficient solution for airports and airlines to grow in a sustainable manner.
Correspondence concerning this publication should be directed to:
AIRBUS S.A.S.
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
Customer ServicesTechnical Data Support and Services1, Rond Point Maurice BELLONTE31707 BLAGNAC CEDEXFRANCE
01-01-00Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
01-02-01 Glossary
**ON A/C A380-800
Glossary
1. List of Abbreviations
A/C Aircraft
ACN Aircraft Classification NumberAPU Auxiliary Power Unit
B/C Business Class
BLG Body Landing Gear
CAS Calibrated Air Speed
CBR California Bearing Ratio
CC Cargo Compartment
CG Center of Gravity
C/L Center Line
E Young’s Modulus
ECS Environmental Control System
FAA Federal Aviation AdministrationF/C First Class
FDL Fuselage Datum Line
FR FrameFSTE Full Size Trolley Equivalent
FWD ForwardGPU Ground Power UnitGSE Ground Support Equipment
ICAO International Civil Aviation Organisation
ISA International Standard Atmosphere
L LeftL Radius of relative stiffnessLCN Load Classification NumberLD Load DeviceLD Lower DeckLH Left HandLPS Last Pax Seating
MAC Mean Aerodynamic Chord
MAX MaximumMD Main DeckMIN Minimum
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
ULD Unit Load DeviceUS United StatesVF Variable Frequency
VFG Variable Frequency Generator
Vref Landing reference speed
WLG Wing Landing Gear
WV Weight Variant
2. Units of Measurement
˚ degree (angle)
% percent
˚C degree Celsius
˚F degree Fahrenheit
bar barcm centimeterdeg degree (angle)
ft footft/s foot per second
ft/s2 foot per square second
ft2 square foot
01-02-01Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
ft3 cubic footin inchkg kilogram
kg/l kilogram per liter
km/h kilometer per hour
kt knotkVA kilovolt ampere
l literlb poundm meterm/s meter per second
m2 square meter
m3 cubic metermin minutemm millimeterMN/m3 meganewton per cubic meter
MPa megapascalnm nautical milepci pound-force per cubic inch
psi pound-force per square incht tonneUS gal United States gallon
3. Design Weight Terminology- Maximum Design Ramp Weight (MRW):
Maximum weight for ground maneuver (including weight of taxi and run-up fuel) as limited byaircraft strength and airworthiness requirements. It is also called Maximum Design Taxi Weight(MTW).
- Maximum Design Landing Weight (MLW):Maximum weight for landing as limited by aircraft strength and airworthiness requirements.
- Maximum Design Takeoff Weight (MTOW):Maximum weight for takeoff as limited by aircraft strength and airworthiness requirements. (Thisis the maximum weight at start of the take-off run).
- Maximum Design Zero Fuel Weight (MZFW):Maximum permissible weight of the aircraft without usable fuel.
- Maximum Seating Capacity:Maximum number of passengers specifically certified or anticipated for certification.
- Usable Volume:Usable volume available for cargo, pressurized fuselage, passenger compartment and cockpit.
- Water Volume:
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
Maximum volume of cargo compartment.- Usable Fuel:
Fuel available for aircraft propulsion.
01-02-01Page 4
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
AIRCRAFT DESCRIPTION
02-01-01 General Aircraft Characteristics Data
**ON A/C A380-800
General Aircraft Characteristics Data
1. The following table provides characteristics of A380-800 Models, these data are specific to eachWeight Variant:
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-02-00 General Aircraft Dimensions
**ON A/C A380-800
General Aircraft Dimensions
1. This section provides General Aircraft Dimensions.
02-02-00Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
72.73 m
70.4 m
53.94 m 4.7 m(15.42 ft)
12.06 m(39.57 ft)
14.5
9 m
8.41 m
14.08 m(46.19 ft)
33.58 m − WLG
36.85 m − BLG
4.97 m(16.31 ft)
(27.59 ft)8.56 m
(28.08 ft)
(176.97 ft)
(230.97 ft)
(238.62 ft)
(47.
87 ft
)12.46 m(40.88 ft)
7.14 m(23.43 ft)
14.34 m
29.6 m
51.4 m
79.75 m
30.37 m(261.65 ft)
(99.64 ft)
5.26 m(17.26 ft)
(47.05 ft)
(97.11 ft)
(168.64 ft)
NOTE: RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.
(110.17 ft)
(120.9 ft)
L_AC_020200_1_0010101_01_02
General Aircraft Dimensions(Sheet 1 of 2)
FIGURE-02-02-00-991-001-A01
02-02-00Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
11.57 m(37.96 ft)
3.72 m(12.2 ft)
17.67 m
72.57 m
68.85 m
46.97 m 3.98 m
29.94 m
22.23 m
(57.97 ft)
(98.23 ft)
(72.93 ft)
(154.1 ft)
52.07 m(170.83 ft)
(13.06 ft)
(225.89 ft)
(238.09 ft)
25.9
7 m
(85.
2 ft)
13.4
9 m
(44.
26 ft
)
17.6
5 m
(57.
91 ft
)21
.87
m(7
1.75
ft)
9.36 m(30.71 ft)
NOTE: RELATED TO AIRCRAFT ATTITUDE AND WEIGHT.L_AC_020200_1_0010103_01_00
General Aircraft Dimensions(Sheet 2 of 2)
FIGURE-02-02-00-991-001-A01
02-02-00Page 3
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-03-00 Ground Clearances
**ON A/C A380-800
Ground Clearances
1. This section gives the heights of various points of the aircraft, above the ground, for different aircraftconfigurations.Dimensions in the tables are approximate and will vary with tire type, weight and balance and otherspecial conditions.
The dimensions are given for:- A light weight, for an aircraft in maintenance configuration with a FWD CG and an AFT CG,- An aircraft at Maximum Ramp Weight with a FWD CG and an AFT CG,- Aircraft on jacks, FDL at 7.2 (23.62 ft).
NOTE : Passenger and cargo door ground clearances are measured from the center of the door silland from floor level.
02-03-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
D
C1
F1
E1
F3
F2
C2
E2
H
G
M2
M3
M5
M4
U1
U2
U3
C3
M1
K2
K1
L4L5
J2J1
L6L3
L2
NO
TE
:F
OR
DIM
EN
SIO
NS
, SE
E S
HE
ET
2.
PA
SS
EN
GE
R A
ND
CA
RG
O D
OO
R G
RO
UN
D C
LEA
RA
NC
ES
AR
E M
EA
SU
RE
DF
RO
M T
HE
CE
NT
ER
OF
TH
E D
OO
R S
ILL
AN
D F
RO
M F
LOO
R L
EV
EL.
L_AC_020300_1_0010101_01_03
Ground Clearances(Sheet 1 of 2)
FIGURE-02-03-00-991-001-A01
02-03-00Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
CO
NF
IGU
RA
TIO
NA
/C C1
C2 D E1
E2 F1
F2
F3 G H J1 J2 K1
K2
L2 L3C3
M2
M3
M4
M5
U1
U2
U3
L4 L5 L6 M1
NO
TE
:M
AX
IMU
M J
AC
KIN
G W
EIG
HT
= 3
33 7
00 k
g (7
35 6
82 lb
).
mft
mft
mft
10.6
10.7
23.5
35.6
36.0
8.0
7.9
6.0
30.5
79.6
27.1
19.6
4.3
7.4
10.7
14.2
11.2
17.1
17.4
17.6
17.8
26.2
26.6
26.7
16.2
17.6
18.5
16.9
A/C
JA
CK
ED
FD
L =
7.2
0 m
(23
.6 ft
)
3.05
3.11
7.13
2.34
2.27
1.66
9.20
24.1
77.
555.
271.
051.
903.
084.
09
3.4
10.0
10.2
23.4
35.3
35.5
7.7
7.4
5.4
30.2
79.3
17.3
6.2
10.1
13.4
4.08
1.08
3.08
3.10
7.17
10.7
910
.78
2.38
2.22
1.66
9.15
24.1
27.
495.
21
1.90
3.07
3.5
10.1
10.2
23.5
35.4
35.4
7.8
7.3
5.4
30.0
79.1
24.6
17.1
6.2
10.1
13.4
3.24
3.27
7.16
10.8
410
.97
2.45
2.41
1.82
9.30
24.2
78.
27
1.30
5.97
2.27
3.27
4.33
10.7
510
.83
24.8
3.24
10.6
3.23
10.6
3.41
5.12
5.15
5.18
5.20
7.87
7.91
7.94
16.8
16.9
17.0
17.1
25.8
26.0
26.0
5.20
5.30
5.37
7.98
8.10
8.15
5.42
4.67
5.01
5.20
5.10
15.3
16.4
17.1
16.7
4.65
4.98
5.17
5.13
15.3
16.3
17.0
16.8
4.95
5.36
5.63
5.14
FW
D C
G(3
7.8%
)A
FT
CG
(41%
)F
WD
CG
(29%
)A
FT
CG
(44%
)
MR
W30
0 t m
ft10
.810
.6
24.3
36.1
35.9
8.5
7.8
6.0
30.2
79.3
27.0
19.5
4.3
7.4
10.7
14.1
11.0
17.5
17.4
17.3
17.3
26.5
26.4
26.3
16.2
17.5
18.4
17.6
3.30
3.23
7.42 11
10.9
32.
592.
381.
829.
2024
.17
8.22
1.30
5.94
2.27
3.26
4.31
3.36
5.34
5.31
5.28
8.08
8.04
8.02
5.27
4.93
5.34
5.61
5.36
mft
16.8
16.8
30.2
42.1
42.1
14.5
14.0
12.1
36.5
85.7
33.2
25.7
10.3
13.5
16.8
20.3
17.2
23.5
23.5
23.5
23.5
32.5
32.5
32.5
22.3
23.7
24.6
23.5
5.12
5.12
9.22
12.8
212
.82
4.41
4.27
3.68
11.1
426
.11
10.1
2
3.14
7.84
4.13
5.12
6.18
5.24
7.15
7.15
7.15
9.90
9.90
9.90
7.15
6.81
7.22
7.50
7.15
16.9
16.9
16.9
16.9
25.9
25.9
26.0
5.14
5.15
5.15
7.89
7.90
7.91
5.16
L_AC_020300_1_0010105_01_01
Ground Clearances(Sheet 2 of 2)
FIGURE-02-03-00-991-001-A01
02-03-00Page 3
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
MAIN DECKTOURIST CLASS 10 ABREAST
MAIN DECKFIRST CLASS 6 ABREAST
(62 in)
1.07 m
(42 in)
0.51 m(20 in)
1.57 m 1.07 m
(42 in) (62 in)1.57 m
(38 in)0.97 m
1.45 m(57 in)
1.45 m(57 in)
1.45 m(57 in)
L_AC_020501_1_0020101_01_00
Interior Arrangements - Cross-sectionTypical Configuration - Main Deck
FIGURE-02-05-01-991-002-A01
02-05-01Page 3
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-06-00 Cargo Compartments
**ON A/C A380-800
Cargo Compartments
1. Cargo Compartments
02-06-00Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-06-01 Location and Dimensions
**ON A/C A380-800
Location and Dimensions - Pax
1. This section gives the cargo compartments location and dimensions of A380-800 models.
02-06-01Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
FO
RW
AR
D A
FT
CA
RG
O
CO
MP
AR
TM
EN
T)
LOW
ER
DE
CK
FO
RW
AR
D C
AR
GO
CO
MP
AR
TM
EN
T
LOW
ER
DE
CK
FO
RW
AR
D A
FT
CA
RG
OC
OM
PA
RT
ME
NT
(T−
SH
AP
ED
LOW
ER
DE
CK
RE
AR
AF
T C
AR
GO
CO
MP
AR
TM
EN
T
LOW
ER
DE
CK
BU
LK C
AR
GO
CO
MP
AR
TM
EN
T
2.8 m(110.2 in)
(110.2 in)
9.7 m(381.9 in)
1.1 m(43.3 in)
3.1 m(122.8 in)
8.2 m(322.8 in)
FR
17F
R44
FR
57F
R90
FR
86F
R17
FR
44F
R57
FR
90F
R86
2.8 m
17.4 m(685.04 in)
L_AC_020601_1_0010101_01_00
Cargo CompartmentsLocation and Dimensions
FIGURE-02-06-01-991-001-A01
02-06-01Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-06-02 Loading Combinations
**ON A/C A380-800
Loading Combinations - Pax
1. This section gives cargo compartments loading combinations.
02-06-02Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
ST
AN
DA
RD
: 20
LD−
3 O
R 7
PA
LLE
TS
88
in /
96 in
X 1
25 in
OP
TIO
N: 2
2 LD
−3
OR
7 P
ALL
ET
S 8
8 in
/ 96
in X
125
inS
TA
ND
AR
D: 1
6 LD
−3
OR
6 L
D−
3 3
PA
LLE
TS
88
in /
96 in
X 1
25 in
OP
TIO
N: 6
PA
LLE
TS
88
in /
96 in
X 1
25 in
L_AC_020602_1_0010101_01_00
Cargo CompartmentsLoading Combinations
FIGURE-02-06-02-991-001-A01
02-06-02Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-07-00 Door Clearances
**ON A/C A380-800
Door Clearances
1. This section gives Door Clearances.
02-07-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
FWDCARGO DOOR
AFTCARGO DOOR
BULKCARGO DOOR
DOORM2L
DOORM1L
DOORU1L
DOORU2L
DOORU3L
DOORM4L
DOORM5L
EMERGENCYEXIT DOOR
M3L
DOORU1R
DOORU2R
DOORU3R
DOORM5R DOOR
M4RDOORM2R
DOORM1R
EMERGENCYEXIT DOOR
M3R
L_AC_020700_1_0010101_01_01
Door ClearancesDoor Location (Sheet 1)
FIGURE-02-07-00-991-001-A01
02-07-00Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
53.63 m(175.95 ft)
49.19 m(161.38 ft)
44.74 m(146.78 ft)
40.3 m(132.22 ft)
20.94 m(68.7 ft)
6.32 m(20.73 ft)
16.5 m(54.13 ft)
11.73 m(38.48 ft)
48.07 m(157.71 ft)
51.09 m(167.62 ft)
32.68 m(107.22 ft)
L_AC_020700_1_0020101_01_01
Door ClearancesDoor Location (Sheet 2)
FIGURE-02-07-00-991-002-A01
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-07-01 Forward Doors
**ON A/C A380-800
Forward Doors
1. This section gives forward doors clearances.
02-07-01Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
SEECHAPTER
2−3
1067 mm(42 in)
(96.5 in)
859 mm(33.8 in)
2451 mm
MAIN DECK DOORM1L, M1R
1891 mm(74.45 in)
45 mm(1.77 in)
MEASURED FROM THE EXTERNAL POINT OFTHE SCUFF PLATE AND THE MOSTEXTERNAL POINT OF THE DOOR SKIN
2137 mm(84.1 in)
2128 mm(83.8 in)
1262 mm(49.7 in)
FREE AISLE
720 mm(28.3 in)
01NOTE:
FREE AISLE
01
01
L_AC_020701_1_0010101_01_00
Door ClearancesForward Doors
FIGURE-02-07-01-991-001-A01
02-07-01Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-07-02 Main and Upper Deck Doors
**ON A/C A380-800
Main and Upper Deck Doors - Pax
1. This section gives main and upper deck doors clearances.
02-07-02Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
UPPER DECK DOORU1L, U2L, U3L, U1R, U2R, U3R
MAIN DECK DOORM2L, M3L, M4L, M2R, M3R, M4R
FWD
45 mm(1.77 in)
SEECHAPTER
2−3MEASURED FROM THE EXTERNAL POINT OF THE SCUFF PLATEAND THE MOST EXTERNAL POINT OF THE DOOR SKIN
01NOTE:
02 ON DOOR M3L/M3R MEASURED FROM THE EXTERNAL POINTOF THE CUTOUT IN THE BELLY FAIRING AND THE MOSTEXTERNAL POINT OF THE BELLY FAIRING FROM THE DOOR
2134 mm(84 in)
SEECHAPTER
2−3
1883 mm(74.1in)FREEAISLE
2124 mm(83.6 in)
1916 mm(75.4 in)
FREEAISLE 2087 mm
(82.2 in)2088 mm(82.2 in)
84 mm(3.31 in)
2453 mm(96.6 in)
1067 mm(42 in)
FREE AISLE
891 mm(35.1 in)ON M3L/M3R702 mm(27.6 in)
2434 mm(95.8 in)
1067 mm(42 in)
FREE AISLE
719 mm(28.3 in)
518 mm(20.4 in)
01
01
1022 mm(40.2 in)ON M3L/M3R840 mm(33.1 in)
01
02
01
02
L_AC_020702_1_0010101_01_00
Door ClearancesMain and Upper Deck Doors - A380-800 Models
FIGURE-02-07-02-991-001-A01
02-07-02Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-07-03 Aft Doors
**ON A/C A380-800
Aft Doors - Pax
1. This section gives aft doors clearances.
02-07-03Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
SEECHAPTER
2−3
1067 mm
2453 mm
1091 mm
(96.6 in)
(42 in)
(43 in)
FWD
45 mm(1.77 in)
MEASURED FROM THE EXTERNAL POINT OFTHE SCUFF PLATE AND THE MOSTEXTERNAL POINT OF THE DOOR SKIN
01NOTE:
MAIN DECK DOORM5L, M5R
FREE AISLE
955 mm(37.6 in)
01
01
1262 mm(49.7 in)
2138 mm(84.2 in)
1883 mm(74.1 in)
FREE AISLE
2124 mm(83.6 in)
L_AC_020703_1_0010101_01_00
Door ClearancesAft Doors - A380-800 Models
FIGURE-02-07-03-991-001-A01
02-07-03Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-07-04 Aft Cargo Compartment Doors
**ON A/C A380-800
Aft Cargo Compartment Doors - Pax
1. This section gives aft cargo compartment doors clearances.
02-07-04Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
SEECHAPTER
2−3
SEECHAPTER
2−3
1752 mm(68.98 in)
2090 mm(82.28 in)
6420 mm(252.76 in) 991 mm
(39.02 in)
1402 mm(55 in)
3071 mm AT FR81A2945 mm AT FR85(121 in) AT FR81A(116 in) AT FR85
FWD
1130 mm(44.49 in)
2794 mm(110 in)
GROUND LINE
2008 mm(79.05 in)
L_AC_020704_1_0010101_01_01
A
A
B
B
A AB B
Door ClearancesAft Cargo Compartment Doors - A380-800 Models
FIGURE-02-07-04-991-001-A01
02-07-04Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-07-05 Forward Cargo Compartment Doors
**ON A/C A380-800
Forward Cargo Compartment Doors - Pax
1. This section gives forward cargo compartment doors clearances.
02-07-05Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
SEECHAPTER
2−3
1752 mm(68.98 in)
6335 mm
(249.41 in)
2118 mm(83.39 in)
(118 in)2986 mm
3111 mm(122.48 in)
FWD
L_AC_020705_1_0010101_01_01
GROUND LINE
2091 mm(82.32 in)
A
A
A A
Door ClearancesForward Cargo Compartment Doors - A380-800 Models
FIGURE-02-07-05-991-001-A01
02-07-05Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-07-06 Nose Landing Gear Doors
**ON A/C A380-800
Nose Landing Gear Doors
1. This section gives nose landing gear doors clearances.
02-07-06Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
AIR
CR
AF
T C
/L
GROUND LINE
A
62°
2.50 m(8.20 ft)
1.36 m(4.46 ft)A
(3.08 ft)
0.94 m
1.89 m(6.20 ft)
L_AC_020706_1_0010101_01_00
Door ClearancesForward Nose Landing Gear Doors
FIGURE-02-07-06-991-001-A01
02-07-06Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
0.75 m (2.46 ft)
A
A
AIR
CR
AF
T C
/L
69.2°
0.50 m (1.64 ft)
1.89 m (6.20 ft)
L_AC_020706_1_0020101_01_00
Door ClearancesAft Nose Landing Gear Doors
FIGURE-02-07-06-991-002-A01
02-07-06Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-07-07 Wing Landing Gear Doors
**ON A/C A380-800
Wing Landing Gear Doors
1. This section gives the wing-landing-gear door clearances.
02-07-07Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
30.91 m(101.41 ft)
(12.96 ft)3.95 m
A
A
LH SHOWNRH SYMMETRICAL
NOTE:* DEPENDING ON CG POSITION AND AIRCRAFT WEIGHT.
GROUND LINE*
MAX 0.25 m (0.82 ft)MIN 0.10 m (0.33 ft)(10.60 ft)
3.23 m
MAX 79°
AIR
CR
AF
T
(5.61 ft)1.71 m
4.28 m(14.04 ft)
2.30 m(7.55 ft)
WING−LANDING−GEARMAIN DOOR
L_AC_020707_1_0010101_01_01
Door ClearancesWing Landing Gear - Main DoorsFIGURE-02-07-07-991-001-A01
02-07-07Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-07-08 Body Landing Gear Doors
**ON A/C A380-800
Body Landing Gear Doors
1. This section gives the body-landing-gear door clearances.
02-07-08Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
(15.49 ft)4.72 m
AIR
CR
AF
TMAX 0.35 m (1.15 ft)MIN 0.25 m (0.82 ft)*
MAX 99°
GROUND LINE
35.67 m(117.03 ft)
(16.96 ft)5.17 m
A
A
LH SHOWNRH SYMMETRICAL
NOTE:* DEPENDING ON CG POSITION AND AIRCRAFT WEIGHT.
(7.38 ft)2.25 m
(16.47 ft)5.02 m
2.90 m(9.51 ft)
BODY−LANDING−GEAROUTER DOOR
L_AC_020708_1_0010101_01_01
Door ClearancesBody Landing Gear - Outer DoorsFIGURE-02-07-08-991-001-A01
02-07-08Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
(4.04 ft)1.23 m
2.25 m(7.38 ft)
GROUND LINE
35.67 m(117.03 ft)
(16.96 ft)5.17 m
A
A
LH SHOWNRH SYMMETRICAL
NOTE:* DEPENDING ON CG POSITION AND AIRCRAFT WEIGHT.
AIR
CR
AF
T
MAX 0.95 m (3.12 ft)MIN 0.70 m (2.30 ft) *
(3.87 ft)1.18 m
1.32 m(4.33 ft)
MAX 94°
BODY−LANDING−GEARCENTER DOOR
L_AC_020708_1_0020101_01_01
Door ClearancesBody Landing Gear - Center Doors
FIGURE-02-07-08-991-002-A01
02-07-08Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-07-09 APU Doors
**ON A/C A380-800
APU Doors
1. This section gives APU doors clearances.
02-07-09Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
GROUND LINE
* DEPENDING ON CG POSITION AND AIRCRAFT WEIGHT
**
FUSELAGE DATUM LINE
MAX 5.52 m (18.10 ft)MIN 5.49 m (18.00 ft)
MAX 6.66 m (21.84 ft)MIN 6.63 m (21.74 ft)
FR112 FR117
L_AC_020709_1_0010101_01_00
Door ClearancesAPU Doors
FIGURE-02-07-09-991-001-A01
02-07-09Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-08-00 Escape Slides
**ON A/C A380-800
Escape Slides
1. GeneralThis section gives location of cabin escape facilities and related clearances.
2. Location
A. Escape facilities are provided at the following locations:
(1) Upper deck evacuation:- One slide-raft at each passenger/crew door (total six).
(2) Main deck evacuation:- One slide-raft at each passenger/crew door (total eight)- One slide for each emergency exit door (total two). The slides are housed in the belly
fairing for off-the-wing evacuation.
02-08-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
MAIN DECK SLIDE
UPPER DECK SLIDE
MAIN DECK SLIDE
UPPER DECK SLIDE
MAIN DECK SLIDE
MAIN DECK SLIDE
UPPER DECKSLIDEOFFWING SLIDE
L_AC_020800_1_0010101_01_00
Escape SlidesLocation
FIGURE-02-08-00-991-001-A01
02-08-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
0
− 3
− 6
− 9
− 1
2
− 1
5
− 1
8
− 2
1
− 2
4
− 2
7
− 3
0
− 3
3
− 3
6
− 3
9
GR
ID E
QU
ALS
1 m
(3.
28 ft
) IN
RE
ALI
TY
− 4
2
EM
ER
GE
NC
Y D
ES
CE
NT
DE
VIC
ET
HR
OU
GH
WIN
DO
W O
PE
NIN
G
L_AC_020800_1_0020101_01_00
Escape SlidesDimensions
FIGURE-02-08-00-991-002-A01
02-08-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-09-00 Landing Gear
**ON A/C A380-800
Landing Gear
1. GeneralThe aircraft has:- Two Wing Landing Gears (WLG) with four wheel bogie assembly and related doors- Two Body Landing Gears (BLG) with six wheel bogie assembly and related doors- A Nose Landing Gear (NLG) with twin wheel assembly and related doors.
The Wing Landing Gears are located under the wing and retract sideways towards the fuselagecenterline.The Body Landing Gears are located on the belly and retract rearward into a bay in the fuselage.The Nose Landing Gear retracts forward into a fuselage compartment below the cockpit.
The landing gear and landing gear doors operation are controlled electrically and are hydraulically andmechanically operated.In abnormal operation, the landing gear can be extended by gravity.
For landing gear footprint and tire size, refer to 07-02-00.
2. Wing Landing GearEach wing landing gear has a leg assembly and a four-wheel bogie beam. The WLG leg includes aBogie Trim Actuator (BTA) and an oleo-pneumatic shock absorber.A two-piece side-stay assembly holds the WLG in the extended position. A lock-stay keeps the side-stay assembly stable in the locked down position.
3. Body Landing GearThe two body landing gears have a six-wheel bogie beam and a leg assembly that includes an oleo-pneumatic shock absorber. A two-piece drag-stay assembly mechanically locks the leg in the extendedposition.
4. Nose Landing GearThe nose landing gear includes a single-stage direct acting oleo-pneumatic shock absorber. A two-piece drag-stay assembly with a lock-stay, mechanically locks the leg in the extended position.
5. SteeringThe wheel steering control system has two parts:- Nose wheel Steering (NWS)- Body Wheel Steering (BWS)Steering is controlled by two hand wheels in the cockpit. For steering angle controlled by the handwheels, refer to AMM 32-51-00 (NWS) and refer to AMM 32-54-00 (BWS).For steering angle limitation, refer to AMM 09-10-00.
02-09-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
A steering disconnection box installed on the nose landing gear to allow steering deactivation fortowing purpose.
6. Landing Gear Servicing Points
A. GeneralFilling of the landing gear shock absorbers is through MS28889 standard valves.Charging of the landing gear shock absorbers is accomplished with nitrogen through MS28889standard valves.
B. Charging PressureFor charging of the landing gear shock absorbers, refer to AMM 32-00-00.
7. Braking
A. GeneralCarbon brakes are installed on each wheel of the WLG and on the wheels of the front andcenter axles of the BLG.The braking system is electrically controlled and hydraulically operated.The braking system has four braking modes plus autobrake and anti-skid systems:- Normal braking with anti-skid capability- Alternative braking with anti-skid capability- Emergency Braking (with Ultimate Braking)- Emergency braking without anti-skid protection is also available as an alternative function of
the alternate braking system.- A park brake system that is manually set is available for the BLG only. This system can also
be used to supply emergency braking.
B. In-Flight Wheel BrakingBraking occurs automatically during the retraction of the landing gear. This stops the rotationof the BLG and WLG wheels (except the wheels on the aft axle of each BLG) before the landinggears go into their related bays.
8. Tire Pressure Indicating System (TPIS)The TPIS automatically monitors the tire pressures and shows these values on Test Equipment(BITE) and also supplies other data and warnings on the WHEEL page of the System Display (SD).The TPIS includes Built In Test Equipment.
9. Built In Test Equipment (BITE)The BITE has these functions, it:- Continuously monitors its systems for failures- Sends failure data (maintenance and warnings) to other systems in the aircraft- Keeps a record of the failures- Automatically does specified tests of the system, or part of the system, at specified times- Lets specified tests to be done during the maintenance procedures.
The BITE for the following systems is described in these chapters:- The Brakes and Steering
02-09-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
- The TPIS- The Landing Gear.
02-09-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
MAIN DOOR(HYDRAULICALLY OPERATED)
AUXILIARY
HINGED DOOR
FAIRING DOOR
A
TIRE INFLATION ADAPTER(EXAMPLE)
E
A
B
WLG LEGASSEMBLY
TORQUELINKS
AFT AXLE
BRAKE RODASSEMBLY
FWDAXLE
BOGIE BEAMASSEMBLY
BOGIE TRIMACTUATOR
SLAVELINKS
SHOCKABSORBER
F
G
DOOR
D
L_AC_020900_1_0050101_01_00
Wing Landing GearGeneral (Sheet 1 of 3)
FIGURE-02-09-00-991-005-A01
02-09-00Page 4
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
WLG DOORACTUATOR
WARNING FLAG
SAFETY COLLAR
GROUND LOCK PIN
SIDE STAYASSEMBLY
UNLOCKACTUATOR
LOCK LINK
DOWNLOCKSPRINGS
QUICK RELEASE PIN
C
C
D
B
L_AC_020900_1_0050102_01_00
Wing Landing GearSafety Devices (Sheet 2 of 3)
FIGURE-02-09-00-991-005-A01
02-09-00Page 5
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
GROUND POINT
E CHARGE VALVE(NITROGEN)
CHECK/FILLVALVE (OIL)
SEAL CHANGEOVERVALVE (COV)
G
F
L_AC_020900_1_0050103_01_00
Wing Landing GearServicing (Sheet 3 of 3)
FIGURE-02-09-00-991-005-A01
02-09-00Page 6
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
INNER DOOR
OUTER DOOR
BLG LEGASSEMBLY
CENTER DOORACTUATOR
DRAG BRACE ASSEMBLY
OUTER DOOR ACTUATOR
CENTER DOOR
A
B
A
(EXAMPLE)
BOGIE TRIMACTUATOR
STEERING
BRAKE ROD
BOGIE/AXLEASSEMBLY
SLAVELINKS
SHOCKABSORBER
OUTERCYLINDER
PINTLE
ACTUATOR
TORQUELINKS
TIRE INFLATIONADAPTOR
FRAME
D
J
H
G
F
G
L_AC_020900_1_0060101_01_00
Body Landing GearGeneral (Sheet 1 of 4)
FIGURE-02-09-00-991-006-A01
02-09-00Page 7
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
INNER DOORACTUATOR
B
C
WARNINGFLAG
SAFETY COLLAR
QUICKRELEASE
PIN
C
L_AC_020900_1_0060102_01_00
Body Landing GearDoor Safety Devices (Sheet 2 of 4)
FIGURE-02-09-00-991-006-A01
02-09-00Page 8
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
WARNINGFLAG
SAFETY STRUT
SAFETY COLLAR
E
QUICKRELEASE
PIN
QUICKRELEASE
PIN
QUICKRELEASE
PIN
LOCKINGPIN
SOLIDPIN
ATTACHMENT PIN
ATTACHMENT PIN
LOCKINGPIN
BLG OUTERDOOR ACTUATOR
CENTER DOORFITTING
E
D
L_AC_020900_1_0060103_01_00
Body Landing GearDoor Safety Devices (Sheet 3 of 4)
FIGURE-02-09-00-991-006-A01
02-09-00Page 9
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
CHARGING VALVE(NITROGEN)
DRAINVALVE
SEAL CHANGEOVERVALVE (COV)
GROUNDINGPOINTS
TYPICAL
F
GROUND LOCK PIN
LOCK SPRINGS
LOCK LINKS
H J
G
L_AC_020900_1_0060104_01_00
Body Landing GearServicing and Safety Device (Sheet 4 of 4)
FIGURE-02-09-00-991-006-A01
02-09-00Page 10
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
B
TOWINGADAPTER
NWSACTUATOR
DOORACTUATOR
FORWARDDOOR
REARDOOR
STEERINGMECHANISM
JACKINGPOINT
MAINTENANCESERVICE PANEL
STEERINGDISCONNECT
PANEL
TIRE INFLATIONADAPTER
A
SHOCKABSORBER
AXLE
TORQUELINKS
MAIN FITTING
C
A
J
E
RETRACTIONACTUATOR
DRAG STAY ASSEMBLY
L
H
L_AC_020900_1_0070101_01_00
Nose Landing GearGeneral (Sheet 1 of 4)
FIGURE-02-09-00-991-007-A01
02-09-00Page 11
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NLG DOORACTUATOR
B
GROUND LOCK PIN
C
LOCK STAY
D
WARNING FLAG
SAFETY COLLAR
QUICKRELEASE PIN
D
UNLOCKACTUATOR
L_AC_020900_1_0070102_01_00
Nose Landing GearSafety Devices (Sheet 2 of 4)
FIGURE-02-09-00-991-007-A01
02-09-00Page 12
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
GROUND TOWING SWITCH
SAFETY PIN
F G
STEERING DISCONNECT PANEL24GC
FG
E
L_AC_020900_1_0070103_01_00
Nose Landing GearSteering Disconnect Panel (Sheet 3 of 4)
FIGURE-02-09-00-991-007-A01
02-09-00Page 13
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
CHARGE VALVE(NITROGEN)
SEAL CHANGEOVERVALVE (COV)
DRAIN VALVE
GROUNDPOINT
J
L
H
K
K
L_AC_020900_1_0070104_01_00
Nose Landing GearServicing (Sheet 4 of 4)
FIGURE-02-09-00-991-007-A01
02-09-00Page 14
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
Landing Gear Maintenance Pits
1. General
The maintenance pit envelopes for the landing gear shock absorber maintenance are shown in Figures1 - 4.The three envelopes show the minimum dimensions for these maintenance operations:- Extension and retraction- Gear removal- Piston removal.
All dimensions shown are minimum dimensions with zero clearances. The dimensions for the pits havebeen determined as follows:- The length and width of the pits allow the gear to rotate as the weight is taken off the landing
gear- The landing gear is in the maximum grown condition- The WLG and BLG bogie beams are removed before the piston is removed- The NLG wheels are removed before the piston is removed- All pistons are removed vertically.
Dimensions for elevators and associated mechanisms must be added to those in Figures 1 - 3.
A. ElevatorsThese can be either mechanical or hydraulic. They are used to:
(1) Permit easy movement of persons and equipment around the landing gears.
(2) To lift and remove landing gear assemblies out of the pits.
B. JackingThe aircraft must be in position over the pits to put the gear on the elevators. Jacks must beinstalled and engaged with all the jacking points, Ref. Section 2-14 for aircraft maintenancejacking. Jacks must support the total aircraft weight, i.e. when the landing gears do not touchthe elevators on retraction/extension tests.When tripod support jacks are used the tripod-base circle radius must be limited because thelocations required for positioning the columns are close to the sides of the pits.
02-09-00Page 15
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
RH
LH
11
3
2
1
10 4
7
5
8 9
13
12
6
L_AC_021000_1_0070101_01_00
Exterior LightingFIGURE-02-10-00-991-007-A01
02-10-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
17 15
14
16
L_AC_021000_1_0080101_01_00
Exterior LightingFIGURE-02-10-00-991-008-A01
02-10-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
2
15 15
3
1
17
88
L_AC_021000_1_0090101_01_00
Exterior LightingFIGURE-02-10-00-991-009-A01
02-10-00Page 4
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
11
1010
16
14
5 5 6
16
9 9
14
L_AC_021000_1_0100101_01_00
Exterior LightingFIGURE-02-10-00-991-010-A01
02-10-00Page 5
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
19 191818
EXAMPLE FOR LIGHT N° 18
CEILING LIGHT
SPOT LIGHT
GROUND
7
7
L_AC_021000_1_0110101_01_00
Exterior LightingFIGURE-02-10-00-991-011-A01
02-10-00Page 6
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-11-00 Antennas and Probes Location
**ON A/C A380-800
Antennas and Probes Location
1. This section gives the location of antennas and probes.
02-11-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
VHF(1)ELTVHF(3)
ADF(2)
ADF(1)
SATCOM(1)
TCAS TOP(2)
TCAS TOP(1)
GPS(1)
GPS(2)
MFP(1)
ISP(1−1)
ISP(3−1)
ISP(2−1) RADIO ALTIMETRE(1)
RADIO ALTIMETRE(2)
RADIO ALTIMETRE(3)
HF
VHF(2)MARKER
VOR
MFP(3)
ISP(2−2)
ISP(1−2)
MFP(2)
STBY STATIC PROBE(2)
TCAS BOTTOM(2)
DME(1) BOTTOM
TCAS BOTTOM(1)
DME(2) BOTTOM
ISP(3−2)
WEATHER RADAR
ICE DETECTOR PROBE RH
SSA(2/3)
SSA(1)
GLIDE TRACK
STBY STATIC PROBE(1)STBY PITOT
LOCGLIDE CAPTURE
ICE DETECTOR PROBE LH
L_AC_021100_1_0010101_01_00
Antennas and ProbesLocation
FIGURE-02-11-00-991-001-A01
02-11-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-12-00 Power Plant
**ON A/C A380-800
Auxiliary Power Unit
1. General- The APU is installed in the tail cone, at the rear part of the fuselage (Section 19.1), inside a
fireproof compartment (between frames 112 and 117).- The Air Intake System is located on top of the APU and crosses the space between the APU
plenum chamber and the aircraft outside (upper right side position). The Air Intake Housing islocated between frames 111 and 113 and the Air Intake Duct is located in the space betweenframes 113 and 115.
- The Exhaust Muffler is located at the end of the tail cone, aligned with the APU and crossesthree different zones, from frame 116 to the rear fairing.
- The Electronic Control Box (ECB) is installed in an electronic cooled rack, closed to frame 95,within the pressurized fuselage.
2. Controls and IndicationPrimary APU controls and indications are installed in the cockpit, mainly in the overhead panel,center pedestal panel and forward center panel. Additionally, two external emergency shutoff controlsare installed on the Nose Landing Gear panel and on the Refuel/Defuel panel.
02-12-00Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
THE DISTANCE FROM FR94, FR98, FR100 BOTTOMCENTERLINE TO FUSELAGE DATUM (FD) AS FOLLOWS:
NOTE:
FR117/
FR112/
FR110/
A
STA72320
STA72922
STA75622
317AB
315AL
313AB
313AZ
FR112 TO FD = 974.9 mm (38.38 in)FR117 TO FD = 1 772.4 mm (69.78 in)FR120 TO FD = 2 239.8 mm (88.18 in).
A B
315BL
315AR
Z310
L_AC_021200_1_0010101_01_00
Auxiliary Power UnitAccess Doors
FIGURE-02-12-00-991-001-A01
02-12-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
EXHAUSTMUFFLER
FIREWALL
FIRE EXTINGUISHERBOTTLE
FIREWALL
AIR INTAKEDUCT ASSEMBLY
COOLING AIR DUCT
BLEEDLINE
FR112/
FR117/
FR110/
STA72922
STA72320
STA75622
B
L_AC_021200_1_0020101_01_00
Auxiliary Power UnitGeneral Layout
FIGURE-02-12-00-991-002-A01
02-12-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
Engine and Nacelle
1. Engine and Nacelle - GP 7200 Engine
A. EngineThe engine is a high by-pass ratio, two-rotor, axial flow turbofan engine with a highcompression ratio. The Engine has Four Major Sections as Follows:- compressor section- combustion section- turbine section- accessory drive section.The compressor section supplies High Pressure (HP) compressed air to the diffuser/burner forcore engine thrust, aircraft service bleed systems, and by-pass air for thrust. A five-stage LowPressure (LP) compressor rotor assembly is located to the rear of the fan rotor. An acousticsplitter fairing directs the primary airstream into the nine-stage HP compressor rotor assembly.The HP compressor has three stages of variable Inlet Guide Vanes (IGVs) and external bleedsfrom stages four, seven, and nine, with an internal bleed from stage six.The combustion section receives compressed heated air from the HP compressor and fuel fromthe fuel nozzles. The mixture of hot air and fuel is ignited and burned in the single-annularcombustion chamber to generate a HP stream of hot gas to turn the HP turbine and LPturbine.The turbine section consists of HP turbine and LP turbine. The two-stage HP turbine rotorassembly receives the hot gas from the diffuser/burner. The HP turbine supplies the power toturn the HP compressor. The six-stage LP turbine has an active clearance control system formore efficient engine operation. The LP turbine provides the power to turn the LP compressorand fan rotor. The Turbine Exhaust Case (TEC) assembly supplies the structural support for therear of the engine. The TEC straightens the exhaust gas flow as it exits the engine.The accessory drive section consists of Main Gearbox (MGB) and Angle Gearbox (AGB). TheMGB supplies the power to turn the attached engine and aircraft accessories. The AGBtransmits the power from the engine rotor to the MGB. During engine start, the AGB transmitsthe power from the MGB to turn the engine rotor.The LP rotor system is independent of the HP rotor system. The LP rotor system consists ofthe LP compressor and the LP turbine. The HP rotor system consists of the HP compressor andthe HP turbine.
B. NacelleThe Nacelle gives an aerodynamic shape to the engine and supports the thrust reverser system.Each engine is housed in a nacelle suspended from a pylon attached below the wing.The nacelle consists of the following major components:
(1) Air Intake Cowl AssemblyThe air intake cowl is an interchangeable aerodynamic cowl installed on the forward faceof the engine fan case with bolts. It is designed to provide contour for airflow entering theengine and attenuates the fan noise.
02-12-00Page 4
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
(2) Fan Cowl AssemblyThe fan-cowl doors are an assembly of aerodynamic cowls attached to the aircraft pylonstructure through its hinges. It is installed between the air intake cowl and the fan exhaustcowl/thrust reverser, around the engine fan case. It is composed of two semicircularpanels, the left and the right fan cowl door.
(3) Thrust ReverserThe thrust reverser assembly is installed at the aft part of the nacelle. The thrust reversercowls are installed on the aircraft inboard engines. It is attached to the wing pylon byhinges. The thrust reverser assembly is a standard fixed cascade, translating cowl andblocker door type thrust reverser. It is only installed on the aircraft inboard positionnacelles. It is made of two halves that make a duct around the engine. Each half consistsof a fixed structure, which gives support for the cascades and actuation system and atranslating cowl.The thrust reverser assembly encloses the engine core with an aerodynamic flow path anduses the outer translating cowl to give a fan exhaust duct and nozzle exit.In stow mode, the thrust reverser is an aerodynamic structure that adds to the enginethrust generation.In reverse mode, it is used to turn and direct the fan exhaust air in the forward directionusing blocker door through the cascades. The thrust reverser increases the aircraft brakingfunction in order to reduce the landing or aborted take-off distance, especially on acontaminated runway.
(4) Fan Exhaust Cowl AssemblyThe fan exhaust cowls is a component of the aircraft propulsion system nacelle. It isinstalled at the aft part of the nacelle. The fan exhaust cowls are installed on the aircraftoutboard engines.The fan exhaust cowls are attached to the wing pylon by hinges. The two halves of the fanexhaust cowl close the engine core with an aerodynamic flow path.The fan exhaust structure has two half-cowls hinged at the top to the wing pylon andlatched together at the bottom centerline. Its forward end is secured on the aft of the fancase and aft of the intermediate engine case.
(5) Exhaust SystemThe primary air flow is the part of the air absorbed by the engine that enters into theengine combustor and that is exhausted to atmosphere through the turbine exhaustsystem.The turbine exhaust flow path is formed by the inner wall of the exhaust nozzle and theouter wall of the exhaust plug.The secondary air flow is the part of the air absorbed by the fan that bypasses the coreengine and flows through the thrust reverser and fan exhaust cowl directly to theatmosphere.
02-12-00Page 5
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
2. Engine and Nacelle -TRENT 900 Engine
A. EngineThe RB211-TRENT 900 engine is a high by-pass ratio, triple spool turbo-fan.The principal modules of the engine are:- Low Pressure Compressor (LPC) rotor- Intermediate Pressure (IP) compressor- Intermediate case- HP system (this includes the High Pressure Compressor (HPC), the combustion system and
the High Pressure Turbine (HPT))- IP turbine- external gearbox- LPC case- Low Pressure Turbine (LPT)The Intermediate Pressure (IP) and Low Pressure Compressor (LPC)/Low Pressure Turbine(LPT) assemblies turn in a counter clockwise direction and the High Pressure Compressor(HPC)/ High Pressure Turbine (HPT) assembly turns in a clockwise direction (when seen fromthe rear of the engine) during engine operation.The compressors increase the pressure of the air, which flows through the engine. The necessarypower to turn the compressors is supplied by turbines.The LP system has a one-stage compressor installed at the front of the engine. A shaft connectsthe single-stage LPC to a five-stage axial flow turbine at the rear of the gas generator. The gasgenerator also includes an eight-stage IP compressor, a six-stage HPC and a combustion system.Each of the compressors in the gas generator is connected to, and turned by, a different turbine.Between the HPC and the HPT is the annular combustion system which burns a mixture of fueland air to supply energy as heat. Behind the LPT there is a collector nozzle assembly throughwhich the hot gas exhaust flows.
B. NacelleA nacelle gives the engine an aerodynamic shape and supports the thrust reverser system. Eachengine is housed in a nacelle suspended from a pylon attached below the wing.The nacelle consists of the following major components:
(1) Air Intake Cowl AssemblyThe air intake cowl is an interchangeable aerodynamic cowl installed at the front of theengine. It ducts the airflow to the fan and the engine core. The cowl has panels for easyaccess to the components. Acoustic materials are used in the manufacture of the cowl tohelp decrease the engine noise.
(2) Fan Cowl AssemblyThe fan cowl assembly has two semicircular panels, the left fan cowl door and the rightfan cowl door. The installation of the fan cowl doors is around the engine fan casebetween the air intake cowl and the thrust reverser cowl.
02-12-00Page 6
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
The fan Cowl Opening System (COS) have two electrical actuators which open or closethe fan cowls. Personnel operate the actuators from the ground only during enginemaintenance operations. The personnel use a switch box located on the air intake cowl.
(3) Thrust ReverserThe thrust reverser assembly is installed at the aft part of the nacelle. The thrust reversersare installed on the aircraft inboard engines. It is attached to the wing pylon by hinges.The thrust reverser assembly is a standard fixed cascade, translating cowl and blocker doortype thrust-reverser. It is only installed on the aircraft inboard engine nacelles. It is madeof two halves that make a duct around the engine. Each half has a fixed structure thatholds the cascades, the actuation system and a translating cowl.The thrust reverser assembly closes the engine core with an aerodynamic flow path anduses the outer translating cowl to make a fan exhaust duct and nozzle exit.In stow mode, the thrust reverser is an aerodynamic structure that makes the enginethrust.In reverse mode, it changes the direction of the fan exhaust air in the forward direction byuse of the blocker doors through the cascades. The thrust reverser increases the aircraftbraking and speed braking function in order to decrease the landing or aborted take-offdistance, especially on a dirty runway.
(4) Fan Exhaust Cowl AssemblyThe fan exhaust cowl is a component of the aircraft engine nacelle. It is installed at the aftpart of the nacelle. The fan exhaust structures are installed on the aircraft outboardengines. They are attached to the wing pylon by hinges. The left and right fan exhauststructures closed the engine core with an aerodynamic flow path. The structure gives a fireprotection and a support for the aerodynamic, inertial and engine loads.The fan exhaust structure has left and right cowls hinged at the top to the wing pylon andlatched together at the bottom centerline. Its forward end is attached at the aft of the fancase.
(5) Exhaust SystemPrimary air is the part of the air absorbed by the fan that enters the engine near the fanblade platform, continues through the Low Pressure (LP) and High Pressure (HP)compressors, the combustor, and the HP and LP turbines, and is accelerated andexhausted to the atmosphere through the turbine exhaust system.The turbine exhaust flow path is formed by the inner surface of the exhaust nozzle and theouter surface of the exhaust plug.Secondary air is the part of the air absorbed by the fan that is directly discharged from theouter portion of the fan, by-passes the core engine and flows through the fan exhaust tothe atmosphere.
02-12-00Page 7
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
3.15 m(10.33 ft)
LPTURBINE
HP COMPRESSOR
COMBUSTORSECTION
2.77 m(9.09 ft)
4.72 m(15.49 ft)
4.93 m(16.17 ft)
TURBINEEXHAUST
CASE
ANGLEGEARBOX
MAINGEARBOX
DRIVE SECTIONACCESSORY
TURBINECENTER FRAME
HPTURBINE
A
A
LP COMPRESSOR
1.93 m(6.33 ft)
L_AC_021200_1_0030101_01_00
Power Plant HandlingEngine Dimensions - GP 7200 Engine
FIGURE-02-12-00-991-003-A01
02-12-00Page 8
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NOSECOWL
INBOARD POSITION
OUTBOARD POSITION
3.8 m(12.47 ft)
A
1.5 m(4.92 ft)
PLUG
PRIMARY NOZZLE
THRUST REVERSERFAN COWL
2.18 m(7.15 ft)
2.52 m(8.27 ft)
1.17 m(3.84 ft)
2.33 m(7.64 ft)
1.31 m(4.3 ft)
A
3.9 m(12.8 ft)
2.11 m(6.92 ft)
L_AC_021200_1_0040101_01_00
Power Plant HandlingNacelle Dimensions - GP 7200 Engine
FIGURE-02-12-00-991-004-A01
02-12-00Page 9
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
45° C
B
ALL ENGINES
6.8 m(22.31 ft)45°
A
MIN. MAX.
A
ENGINE 1−4
2.64 m(8.66 ft)
B
3.14 m(10.3 ft)
MIN. MAX.
ENGINE 2−3
1.86 m(6.1 ft)
2.16 m(7.09 ft)
C
SEE AC SECTION2−3−0
NOTE:
: FAN COWL
1 1
B AND C DEPENDING ON AIRCRAFT CONFIGURATION.
1
A
A
AA
A
POSITIONOPEN
L_AC_021200_1_0050101_01_00
Power Plant HandlingFan Cowls - GP 7200 Engine
FIGURE-02-12-00-991-005-A01
02-12-00Page 10
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
6.32 m(20.73 ft)45°
AMIN. MAX.
1.86 m(6.1 ft)
B
2.16 m(7.09 ft)
SEE AC SECTION2−3−0
NOTE:
5.8 m(19.03 ft)35°
1.52 m(4.99 ft)
1.82 m(5.97 ft)
C
: THRUST REVERSER1
B AND C DEPENDING ON AIRCRAFT CONFIGURATION.
45°35°C
BC
B
A A11
1 1
A
A
A
POSITIONOPEN
L_AC_021200_1_0060101_01_00
Power Plant HandlingThrust Reverser Cowls - GP 7200 Engine
FIGURE-02-12-00-991-006-A01
02-12-00Page 11
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NOTE: B AND C DEPENDING ON AIRCRAFT CONFIGURATION.
6.32 m(20.73 ft)
AMIN. MAX.
2.64 m(8.66 ft)
3.14 m(10.3 ft)
SEE AC SECTION2−3−0
5.8 m(19.03 ft)
2.3 m(7.55 ft)
2.8 m(9.19 ft)
CB
: FAN EXHAUST COWL
45°35°C
BC
B
A A
A
A
A
1 11 1
1
45°
35°
POSITIONOPEN
L_AC_021200_1_0070101_01_00
Power Plant HandlingFan Exhaust Cowls - GP 7200 Engine
FIGURE-02-12-00-991-007-A01
02-12-00Page 12
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
1.88 m(6.17 ft)
5.14 m(16.86 ft)
1.5 m(4.92 ft)
(2.59 ft)
8.07 m(26.48 ft)
IP COMPRESSOR
SECTIONCOMBUSTOR
IP TURBINE
HP TURBINE
HP COMPRESSOR
ACCESSORY DRIVE SECTION
1.66 m(5.45 ft)
PLUG
3.11 m(10.2 ft)
LP COMPRESSOR
0.79 m
LP TURBINE
NOZZLETURBINE EXHAUST
1.84 m(6.04 ft)
A
A
L_AC_021200_1_0080101_01_00
Power Plant HandlingEngine Dimensions - TRENT 900 Engine
FIGURE-02-12-00-991-008-A01
02-12-00Page 13
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
INBOARD
OUTBOARD
INSTALLATION
INSTALLATION
PLUG
PRIMARY NOZZLE
THRUST REVERSER
FAN COWL
NOSE COWL
2.38 m(7.81 ft)
3.9 m(12.8 ft)
1.18 m(3.87 ft)
3.88 m(12.73 ft)
1.3 m(4.27 ft)
1.63 m(5.35 ft)
2.18 m(7.15 ft)
2.39 m(7.84 ft)
A
A
FWD
2.19 m(7.19 ft)
L_AC_021200_1_0090101_01_00
Power Plant HandlingNacelle Dimensions - TRENT 900 Engine
FIGURE-02-12-00-991-009-A01
02-12-00Page 14
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
Power Plant HandlingFan Cowls - TRENT 900 EngineFIGURE-02-12-00-991-010-A01
02-12-00Page 15
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NOTE: B AND C DEPENDING ON AIRCRAFT CONFIGURATION.
6.32 m(20.73 ft)
AMIN. MAX.
1.86 m(6.1 ft)
B
2.16 m(7.09 ft)
SEE AC SECTION2−3−0
5.8 m(19.03 ft)
1.52 m(4.99 ft)
1.82 m(5.97 ft)
C
: THRUST REVERSER1
45°35°C
BC
B
A A11
1 1
A
A
A
45°
35°
POSITIONOPEN
L_AC_021200_1_0110101_01_00
Power Plant HandlingThrust Reverser Cowls - TRENT 900 Engine
FIGURE-02-12-00-991-011-A01
02-12-00Page 16
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NOTE:
1
B AND C DEPENDING ON AIRCRAFT CONFIGURATION.
6.32 m(20.73 ft)
AMIN. MAX.
2.64 m(8.66 ft)
3.14 m(10.3 ft)
SEE AC SECTION2−3−0
5.8 m(19.03 ft)
2.3 m(7.55 ft)
2.8 m(9.19 ft)
C
: FAN EXHAUST COWL
B
45°35°C
BC
B
A A11
1 1
A
A
A
45°
35°
POSITIONOPEN
L_AC_021200_1_0120101_01_00
Power Plant HandlingFan Exhaust Cowls - TRENT 900 Engine
FIGURE-02-12-00-991-012-A01
02-12-00Page 17
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-13-00 Leveling, Symmetry and Alignment
**ON A/C A380-800
Leveling, Symmetry and Alignment
1. Quick LevelingThere are three alternative procedures to level the aircraft:- Quick leveling procedure with Air Data/Inertial Reference System (ADIRS).- Quick leveling procedure with a spirit level in the upper or main deck passenger compartment.- Quick leveling procedure with a spirit level in the FWD cargo compartment.
2. Precise LevelingFor precise leveling, it is necessary to install sighting rods in the receptacles located under thefuselage (points 11 and 16 for longitudinal leveling) and under the wings (points 1L and 1R for lateralleveling) and use a sighting tube. With the aircraft on jacks, adjust the jacks until the referencemarks on the sighting rods are aligned in the sighting plane (aircraft level).
3. Symmetry and Alignment CheckPossible deformation of the aircraft is measured by photogrammetry.
02-13-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
FR35FR36
FR88
FR89
RIB6
RIB61L
11
1R
16
L_AC_021300_1_0010101_01_00
Location of Leveling PointsFIGURE-02-13-00-991-001-A01
02-13-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
02-14-00 Jacking
**ON A/C A380-800
Jacking for Maintenance
1. Aircraft Jacking Points for Maintenance
A. General
(1) The A380-800 can be jacked:- At not more than 333 700 kg (735 682 lb)- Within the limits of the permissible wind speed when the aircraft is jacked outside a
closed environment.
B. Primary Jacking Points
(1) The aircraft is provided with three primary jacking points:- One located under the forward fuselage- Two located under the wings (one under each wing).
(2) Three jack adapters (ground equipment) are used as intermediary parts between theaircraft jacking points and the jacks:- One male spherical jack adapter at the forward fuselage- Two female spherical jack pad adapters at the wings (one at each wing).
C. Auxiliary Jacking Point (Safety Stay)
(1) When the aircraft is on jacks, a safety stay is installed under the AFT fuselage (Ref. Fig.Jacking Point Location) to prevent tail tipping caused by accidental displacement of theaircraft center of gravity.
(2) The safety point must not be used for lifting the aircraft.
(3) One male spherical stay adapter (ground equipment) is used as an intermediary partbetween the aircraft safety point and the stay.
2. Jacks and Safety Stay
A. Jack Design
(1) The maximum eligible loads given in the table (Ref. Fig. Jacking Point Location) are themaximum loads applicable on jack fittings.
(2) In fully retracted position (jack stroke at minimum), the height of the jacks is such thatthe jack may be placed beneath the aircraft under the most adverse conditions, namely,tires deflated and shock absorbers depressurized, with sufficient clearance between theaircraft jacking point and the jack upper end.
(3) The jacks stroke enables the aircraft to be jacked up so that the Fuselage Datum Line(FDL) may be positioned up to 7 200 mm (283.46 in) from the ground to allow allrequired maintenance procedures and in particular, the removal/installation of the landing-gear shock absorbers.
02-14-00Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
B. Safety Stay
(1) The stay stroke enables the aircraft tail to be supported up to the Fuselage Datum Line(FDL) positioned 7 200 mm (283.46 in) from the ground.
02-14-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
FWD JACKINGPOINT
WING JACKINGPOINT
SAFETYSTAY
Y
X
A C
B’
B
NOTE: SAFETY STAY IS NOT USED FOR JACKING.
SAFETY STAY
WING JACKINGPOINT
C
B’
B
FORWARD FUSELAGEJACKING POINT A
7.29 23.92 0
12.22
−12.22
0
0
40.09
−40.09
0
MAXIMUMLOAD ELIGIBLE
m ft daN
YX
m ft
35.23
35.23
59.34
115.58
115.58
194.68
34 011
157 480
157 480
7 874
WING JACKINGPOINT
L_AC_021400_1_0010101_01_00
Jacking for MaintenanceJacking Points Location
FIGURE-02-14-00-991-001-A01
02-14-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
AIRCRAFT ON WHEELS WITH STANDARD TIRES, MAX. JACKWEIGHT 333 700 kg (735 682 lb)AIRCRAFT ON WHEELS, SHOCK ABSORBERS DEFLATED ANDTIRES FLAT
AIRCRAFT ON WHEELS, NOSE LANDING GEAR SHOCKABSORBERS DEFLATED AND TIRES FLAT
AIRCRAFT ON WHEELS, LEFT WING AND BODY LANDINGGEARS SHOCK ABORBERS DEFLATED AND TIRES FLAT (SAMEDATA FOR RIGHT SIDE CONDITIONS)AIRCRAFT ON WHEELS, WING AND BODY LANDING GEARSSHOCK ABSORBERS DEFLATED AND TIRES FLAT
AIRCRAFT ON JACKS, FUSELAGE DATUM LINEPARALLEL TO GROUND AT 6 350 mm (250 in) FOR LANDINGGEARS EXTENSION/RETRACTION
2 472 mm(97.32 in)
2 259 mm(88.94 in)
2 296 mm(90.39 in)
2 474 mm(97.4 in)
2 391mm(94.13 in)
3 673 mm(144.61 in)
5 112 mm(201.26 in)
4 788 mm(188.5 in)
5 117 mm(201.46 in)
4 523 mm(178.07 in)
4 803 mm(189.09 in)
6 158 mm(242.44 in)
4 707 mm(185.31 in)
4 462 mm(175.67 in)
5 044 mm(198.58 in)
4 257 mm(167.6 in)
4 291 mm(168.94 in)
5 830 mm(229.53 in)
AIRCRAFT ON JACKS, FUSELAGE DATUM LINEPARALLEL TO GROUND AT 7 200 mm (283.46 in) FOR LANDINGGEARS REMOVAL/INSTALLATION
L M N
4 523 mm(178.07 in)
7 008 mm(275.91 in)
6 680 mm(262.99 in)
LN
FUSELAGE DATUM LINE
M
AIRCRAFT JACKED AT FORWARD JACKING POINT,WING AND BODY LANDING GEARS WHEELS ON THE GROUND,FOR NOSE LANDING GEAR EXTENSION/RETRACTION TEST
4 523 mm(178.07 in) N/A 2 910 mm
(114.57 in)
L_AC_021400_1_0020101_01_01
Jacking for MaintenanceJacking Dimensions
FIGURE-02-14-00-991-002-A01
02-14-00Page 4
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
FR20
A
B
A
ADAPTOR−JACK NOSE
Z−2676.63
B
L_AC_021400_1_0030101_01_00
Jacking for MaintenanceForward Jacking Point
FIGURE-02-14-00-991-003-A01
02-14-00Page 5
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
RIB16
OUTER SKIN
JACKING PAD SET− WING
B
AEXAMPLE
Z−147
B
A
ARIB16RIB16
LOWER SURFACE
L_AC_021400_1_0100101_01_00
Jacking for MaintenanceWing Jacking Point
FIGURE-02-14-00-991-010-A01
02-14-00Page 6
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
FR101
A
ADAPT−SUPP, AFT JACK
FR101
A
Z−519.589
FWD
L_AC_021400_1_0110101_01_00
Jacking for MaintenanceAuxiliary Jacking Point - Safety Stay
FIGURE-02-14-00-991-011-A01
02-14-00Page 7
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
Jacking for Wheel Change
1. To replace a wheel or wheel brake assembly on any of the landing gears it is necessary to lift thelanding gear with a jack. The landing gear can be lifted by a pillar jack or with a cantilever jack.
NOTE : You can lift the aircraft at Maximum Ramp Weight (MRW).
A. Nose Landing Gear (NLG)The nose gear can be lifted with a pillar jack or a cantilever jack. The NLG has a dome shapedjacking adaptor at the base of the shock absorber strut. The adapter is 31.75 mm (1.25 in) indiameter.Important dimensions of the NLG when lifted are shown in Fig. 001.The reaction loads at the jacking position are shown in Fig. 004.
NOTE : The load at each jacking position is the load required to give a 25.5 mm (1 in)clearance between the ground and the tire.
B. Wing Landing Gear (WLG)An adapter at the front and rear of each bogie is fitted to make sure that the jack is locatedcorrectly. The adapter is 31.75 mm (1.25 in) in diameter. The wheels and brake units can bereplaced on the end of the bogie beam that is lifted.The FWD and AFT ends of the bogie can be lifted at the same time. When lifting both ends atthe same time the bogie beam must always be kept level to prevent damage.If a WLG has all four tires deflated or shredded, replace the wheel assemblies in this sequence:- Replace the wheel assemblies on the AFT axle- Replace the wheel assemblies on the FWD axle.
Important dimensions of the WLG when lifted are shown in Fig. 002.The reaction loads at the jacking position are shown in Fig. 005.
NOTE : The load at each jacking position is the load required to give a 25.5 mm (1 in)clearance between the ground and the tire.
C. Body Landing Gear (BLG)An adapter at the front and at the rear of each bogie is fitted to make sure that the jack islocated correctly. The adapter is 31.75 mm (1.25 in) in diameter. Both wheels and brake unitscan be replaced on the end of the bogie beam that is lifted.For a center wheel change only, the FWD and AFT ends of the bogie can be lifted at the sametime. When lifting both ends at the same time the bogie beam must always be kept level toprevent damage.If a BLG has all six tires deflated or shredded, replace the wheel assemblies in this sequence:- Replace the wheel assemblies on the AFT axle- Replace the wheel assemblies on the center axle- Replace the wheel assemblies on the FWD axle.
02-14-00Page 8
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
Important dimensions of the BLG when lifted are shown in Fig. 003.The reaction loads at the jacking position are shown in Fig. 006.
NOTE : The load at each jacking position is the load required to give a 25.5 mm (1 in)clearance between the ground and the tire.
02-14-00Page 9
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
DATA FOR 1 270 x 455 R22 TIRES
MRW = 562 000 kg (1 238 998 lb)MLW = 386 000 kg (850 984 lb)
NOTE: DIMENSIONS IN MILLIMETERS (INCHES IN BRACKETS)
VIEW LOOKING INBOARD LHS(LH WHEEL NOT SHOWN) A
B
CONFIGURATION WEIGHT CG%
MRW 43
MRW 43
MLW−PAX
44
DIM. B
2 INFLATED TIRES 400 (15.75)
DIM. A
541 (21.3)
1 INFLATED TIRE 353 (13.9) 530 (20.87)
2 DEFLATED TIRES +50%RIM DAMAGE
29 134 (5.28) 519 (20.43)
2 DEFLATED TIRESNO RIM DAMAGE
2 DEFLATED TIRES +50%RIM DAMAGE
136 (5.35) 519 (20.43)
519 (20.43)29 164 (6.46)
N/A N/A
N/A N/A
MAXIMUM JACKINGHEIGHT TO CHANGEWHEELS
N/A 506 (19.92) N/A
168 (6.61)
137 (5.39)
166 (6.54) 519 (20.43)
519 (20.43)
519 (20.43)
2 DEFLATED TIRESNO RIM DAMAGE
44
20 DEFLATED TIRES +50%RIM DAMAGE
20 DEFLATED TIRESNO RIM DAMAGE
N/A
MLW−PAX
MLW−PAX
MLW−PAX
L_AC_021400_1_0040101_01_00
Nose Landing Gear Jacking Point HeightsFIGURE-02-14-00-991-004-A01
02-14-00Page 10
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
NOTE: THESE CURVES ARE GIVEN FOR INFORMATION ONLY.THE APPROVED VALUES ARE STATED IN THE "OPERATING MANUALS"SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.
100
120
PA
YLO
AD
(x
1000
lb)
200 nm DIVERSION5% TRIP FUEL ALLOWANCE, 30 min HOLDING
L_AC_030201_1_0010101_01_00
Payload/RangeISA Conditions - TRENT 900 Engines
FIGURE-03-02-01-991-001-A01
03-02-01Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
NOTE: THESE CURVES ARE GIVEN FOR INFORMATION ONLY.THE APPROVED VALUES ARE STATED IN THE "OPERATING MANUALS"SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.
PA
YLO
AD
(x
1000
lb)
200 nm DIVERSION5% TRIP FUEL ALLOWANCE, 30 min HOLDING
L_AC_030201_1_0080101_01_00
Payload/RangeISA Conditions - GP 7200 EnginesFIGURE-03-02-01-991-008-A01
03-02-01Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
03-03-01 Take Off Weight Limitation - ISA Conditions
**ON A/C A380-800
FAA/EASA Take Off Weight Limitation - Pax
1. This section gives the take-off weight limitation at ISA conditions.
03-03-01Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NOTE: THESE CURVES ARE GIVEN FOR INFORMATION ONLY.THE APPROVED VALUES ARE STATED IN THE "OPERATING MANUALS"SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NOTE: THESE CURVES ARE GIVEN FOR INFORMATION ONLY.THE APPROVED VALUES ARE STATED IN THE "OPERATING MANUALS"SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.
FAA/EASA Take-Off Weight LimitationISA Conditions - GP 7200 EnginesFIGURE-03-03-01-991-008-A01
03-03-01Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
03-03-02 Take Off Weight Limitation - ISA + 15 ˚C (59 ˚F)
**ON A/C A380-800
FAA/EASA Take Off Weight Limitation - ISA + 15 ˚C (59 ˚F)
1. This section gives the take-off weight limitation at ISA +15˚C (59˚F) conditions.
03-03-02Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NOTE: THESE CURVES ARE GIVEN FOR INFORMATION ONLY.THE APPROVED VALUES ARE STATED IN THE "OPERATING MANUALS"SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NOTE: THESE CURVES ARE GIVEN FOR INFORMATION ONLY.THE APPROVED VALUES ARE STATED IN THE "OPERATING MANUALS"SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
03-04-01 Landing Field Length
**ON A/C A380-800
FAA/EASA Landing Field Length
1. This section gives the landing field length on a dry runway.
03-04-01Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NOTE: THESE CURVES ARE GIVEN FOR INFORMATION ONLY.THE APPROVED VALUES ARE STATED IN THE "OPERATING MANUALS"SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.
1400
1500
1600
1700
1800
1900
2000
2100
2200
2300
2400
2500
2600
2700
2800
280 300 320 340 360 380 400 420 440 4604600
5000
5400
5800
6200
6600
7000
7400
7800
8200
8600
9000
620 670 720 770 820 870 920 970
GROSS WEIGHT (t)
VALID FOR ALL TEMPERATURES
AIRFIELD ELEVATION (ft)
0
2000
6000
4000
8000
LAN
DIN
G F
IELD
LE
NG
TH
(ft)
LAN
DIN
G F
IELD
LE
NG
TH
(m
)
GROSS WEIGHT (x 1000 lb)
L_AC_030401_1_0010101_01_01
FAA/EASA Landing Field LengthDry Runway
FIGURE-03-04-01-991-001-A01
03-04-01Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
03-05-00 Final Approach Speed
**ON A/C A380-800
Final Approach Speed
1. This section gives the final approach speed which is the indicated airspeed at threshold in the landingconfiguration at the certificated maximum flap setting and maximum landing weight at standardatmospheric conditions. The approach speed is used to classify the aircraft into Aircraft ApproachCategory, a grouping of aircraft based on the indicated airspeed at threshold.
2. The final approach speed is 138 kt at a Maximum Landing Weight (MLW) of 395 000 kg (870 826lb) and classifies the aircraft into the Aircraft Approach Category C.
NOTE : This value is given for information only.
03-05-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
GROUND MANEUVERING
04-01-00 General Information
**ON A/C A380-800
General
1. This section provides aircraft turning capability and maneuvering characteristics.
For ease of presentation, this data has been determined from the theoretical limits imposed by thegeometry of the aircraft, and where noted, provides for a normal allowance for tire slippage. As such,it reflects the turning capability of the aircraft in favorable operating circumstances. This data shouldonly be used as a guidelines for the method of determination of such parameters and for themaneuvering characteristics of this aircraft type.
In ground operating mode, varying airline practices may demand that more conservative turningprocedures be adopted to avoid excessive tire wear and reduce possible maintenance problems. Airlineoperating techniques will vary in the level of performance, over a wide range of operatingcircumstances throughout the world. Variations from standard aircraft operating patterns may benecessary to satisfy physical constraints within the maneuvering area, such as adverse grades, limitedarea or a high risk of jet blast damage. For these reasons, ground maneuvering requirements shouldbe coordinated with the airlines in question prior to layout planning.
04-01-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
04-02-00 Turning Radii
**ON A/C A380-800
Turning Radii
1. This section gives the turning radii.
04-02-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NOTE:
R4
R3
R5
R6
SEE PAGE 2 FOR DIMENSIONS
55°
60°
65°
29.83 m ( 97.9 ft )
70°
L_AC_040200_1_0010101_01_00
Turning RadiiTurning Radii (Sheet 1)
FIGURE-04-02-00-991-001-A01
04-02-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
2 100.16328.6
TYPEOF
TURN
20
STEERINGANGLE
17.9
EFFECTIVESTEERING
ANGLE
mft
135.45444.4
101.01331.4
115.87380.1
2 78.86258.7
25 22.7 mft
113.14371.2
80.12262.9
94.90311.4
2 65.69215.5
30 27.5 mft
98.90324.5
67.33220.9
81.91268.7
2 56.84186.5
35 32.1 mft
88.97291.9
58.83193.0
73.13239.9
2 50.59166.0
40 36.6 mft
81.61267.8
52.89173.5
66.84219.3
2 46.02151.0
45 41.0 mft
75.94249.1
48.61159.5
62.16203.9
2 42.61139.8
50 45.1 mft
71.43234.4
45.45149.1
58.57192.2
1 40.13131.6
55 51.2 mft
67.02219.9
43.22141.8
55.43181.9
1 37.64123.5
60 57.3 mft
62.60205.4
40.98134.5
52.29171.5
1 35.15115.3
65 63.4 mft
58.18190.9
38.75127.1
49.15161.2
1 32.66107.2
70 69.5 mft
53.76176.4
36.52119.8
46.01150.9
R3 R4 R5 R6
A380−800/800F TURNING RADII
NOTE:
TYPE 1 TURNS USE :ASYMMETRIC THRUST − BOTH ENGINES ON THE INSIDE OF THE TURN TO BE AT IDLE THRUSTDIFFERENTIAL BRAKING − BRAKING APPLIED TO THE WING GEAR WHEELS ON THE INSIDE OF
TYPE 2 TURNS USE :SYMMETRIC THRUST AND NO BRAKING.
THE TURN.
L_AC_040200_1_0020101_01_00
Turning RadiiTurning Radii (Sheet 2)
FIGURE-04-02-00-991-002-A01
04-02-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
04-03-00 Minimum Turning Radii
**ON A/C A380-800
Minimum Turning Radii
1. This section gives the minimum turning radii.
04-03-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
AR4
R3
R5
Y
R6
(TU
RN
ING
WID
TH
)
55°
60°
65°
29.83 m ( 97.9 ft )
70°
TURN PERFORMED WITH ASYMMETRIC THRUST AND DIFFERENTIAL BRAKINGNOTE:
EffectiveSteering
AngleY
m
ft70° 69.5°
A380−800/800F Minimum Turning Radius
SteeringAngle
Typeof
Turn
11.08
36.3
A
50.91
167.0
R3
32.66
107.2
R4
53.76
176.4
R5
36.52
119.8
R6
46.01
150.91
L_AC_040300_1_0010101_01_01
Minimum Turning RadiiFIGURE-04-03-00-991-001-A01
04-03-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
04-04-00 Visibility from Cockpit in Static Position
**ON A/C A380-800
Visibility from Cockpit in Static Position
1. This section gives the visibility from cockpit in static position.
04-04-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
PERPENDICULAR TOLONGITUDINAL AXIS.
VISUAL ANGLES IN VERTICALPLANE THROUGH PILOTEYE POSITION.
DIMENSIONS ARE APPROXIMATE
107°
CAPTAIN FIELD OF VIEW
121°
107°
MAX AFT VISION WITH HEAD TURNEDAROUND SPINAL COLUMN.WING TIP CAN BE SEEN WHEN HEAD IS MOVEDTO THE SIDE.
VISUAL ANGLES IN HORIZONTALPLANE THROUGH PILOTEYE POSITION.
FIRST OFFICERFIELD OF VIEW
30°
24°
VISUAL ANGLES IN PLANE
30°
121°
NOT TO BE USED FORLANDING APPROACH VISIBILITY
NOTE:PILOT EYE POSITION WHEN PILOT’S EYES ARE IN LINE WITH THE RED AND WHITE BALLS.
ZONE THAT CANNOT BE SEEN
17.36 m(56.96 ft)
4.97 m(16.31 ft)
2.92 m(9.58 ft)7.17 m
(23.52 ft)
31°
19.5°
24°
L_AC_040400_1_0010101_01_01
Visibility from Cockpit in Static PositionFIGURE-04-04-00-991-001-A01
04-04-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
CA
PT
AIN
FIE
LD O
F V
IEW
SH
OW
N.
FIR
ST
OF
FIC
ER
FIE
LD O
F V
IEW
SY
MM
ET
RIC
AL.
EX
AM
PLE
: WH
EN
CA
PT
AIN
TU
RN
S H
IS H
EA
D B
Y 9
0° L
EF
T, V
ISIB
ILIT
YW
ILL
BE
30°
UP
AN
D 2
4° D
OW
N T
HR
OU
GH
TH
E S
LID
ING
WIN
DO
W F
RA
ME
.
CA
PT
AIN
FIX
ED
WIN
DO
W
130°
120°
110°
100°
90°
80°
70°
60°
50°
40°
30°
20°
10°
0°10
°20
°30
°40
°50
°60
°70
°80
°90
°100
°110
°120
°130
°140
°
30°
20°
10°
0°10°
20°
30°
40°
50°
CA
PT
AIN
SLI
DIN
GW
IND
OW
CA
PT
AIN
WIN
DS
HIE
LD
FIR
ST
OF
FIC
ER
WIN
DS
HIE
LDF
IRS
T O
FF
ICE
RF
IXE
D W
IND
OW
FIR
ST
OF
FIC
ER
SLI
DIN
G W
IND
OW
PIL
OT
EY
E P
OS
ITIO
N(C
AP
TA
IN P
OS
ITIO
N)
A38
0
AR
P 4
101−
2
24°
150°
L_AC_040400_1_0020101_01_00
Binocular Visibility Through Windows from Captain Eye PositionFIGURE-04-04-00-991-002-A01
04-04-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
04-05-00 Runway and Taxiway Turn Paths
**ON A/C A380-800
Runway and Taxiway Turn Paths
1. Runway and Taxiway Turn Paths
04-05-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
04-05-01 135˚ Turn - Runway to Taxiway
**ON A/C A380-800
135˚ Turn - Runway to Taxiway
1. This section gives the 135˚ turn -- runway to taxiway.
04-05-01Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
APPROX 6.6 m(22 ft)
FILLET R = 25.5 m(85 ft)
TURN R = 45 m(150 ft)
APPROX 4.9 m(16 ft)
OFFSET 7 m(23 ft)
NOMINAL
45 m(150 ft)
23 m(75 ft)
RUNWAYCENTERLINE TAXIWAY CENTERLINE
FAA LEAD−IN FILLET
L = 75 m (250 ft)
NOTE: FAA GROUP V FACILITIES.
NLG PATH
WLG PATH
COCKPIT PATH
L_AC_040501_1_0010101_01_01
135˚ Turn -- Runway to TaxiwayJudgemental Oversteer MethodFIGURE-04-05-01-991-001-A01
04-05-01Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NLG PATH
WLG PATH
NOTE: FAA GROUP VI FACILITIES.
FILLET R = 25.5 m(85 ft)
APPROX 5.8 m(19 ft)
TURN R = 51 m(167 ft)
60 m(200 ft)
30 m(100 ft)
RUNWAY CENTERLINE
TAXIWAY CENTERLINE
FAA LEAD−IN FILLET
L = 75 m (250 ft)
L_AC_040501_1_0020101_01_01
135˚ Turn -- Runway to TaxiwayCockpit Tracks Centreline MethodFIGURE-04-05-01-991-002-A01
04-05-01Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
04-05-02 90˚ Turn - Runway to Taxiway
**ON A/C A380-800
90˚ Turn - Runway to Taxiway
1. This section gives the 90˚ turn -- runway to taxiway.
04-05-02Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
23 m(75 ft)
45 m(150 ft)
RUNWAY CENTERLINE
APPROX 9.2 m(30 ft)
FILLET R = 25.5 m(85 ft)
TURN R = 45 m(150 ft)
APPROX 10 m(33 ft)
APPROX 7 m(23 ft)
TAXIWAYCENTERLINE
FAA LEAD−IN FILLETL = 75 m (250 ft)
NOTE: FAA GROUP V FACILITIES.
NLG PATH
WLG PATH
COCKPIT PATH
L_AC_040502_1_0010101_01_01
90˚ Turn -- Runway to TaxiwayJudgemental Oversteer MethodFIGURE-04-05-02-991-001-A01
04-05-02Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
TURN R = 51 m(167 ft)
30 m
(100
ft)
60 m(200 ft)
RUNWAY CENTERLINE
FILLET R = 25.5 m(85 ft)
APPROX 10.2 m(33 ft)
TAXIWAYCENTERLINE
FAA LEAD−IN FILLETL = 75 m (250 ft)
NOTE: FAA GROUP VI FACILITIES.
NLG PATH
WLG PATH
L_AC_040502_1_0020101_01_01
90˚ Turn -- Runway to TaxiwayCockpit Tracks Centreline MethodFIGURE-04-05-02-991-002-A01
04-05-02Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
04-05-03 180˚ Turn on a Runway
**ON A/C A380-800
180˚ Turn on a Runway
1. This section gives the 180˚ turn on a runway.
04-05-03Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NOTE:
4.5 m(15 ft)
4.5 m(15 ft)
0.7 m(2 ft)
16.8 m(55 ft)
31.2 m(102 ft)
23.2 m(76 ft)
R4 = 54 m(177 ft)
R5 = 36.6 m(120 ft)
R6 = 46 m(151 ft)
51 m(167 ft)
60 m(200 ft)
RUNWAYCENTERLINE
NLG PATH
WLG PATH
NOSE TIP PATH
WING TIP PATH
TAIL TIP PATH
R3 = 32.7 m(107 ft)
NLG WHEELOUTER−FACE PATH70° NOSE GEAR STEERING − ASYMMETRIC THRUST AND BRAKING
ON A 60 m (200 ft) WIDE RUNWAY.L_AC_040503_1_0010101_01_01
180˚ Turn on a RunwayFIGURE-04-05-03-991-001-A01
04-05-03Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
04-05-04 90˚ Turn - Taxiway to Taxiway
**ON A/C A380-800
90˚ Turn - Taxiway to Taxiway
1. This section gives the 90˚ turn - taxiway to taxiway.
04-05-04Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
TAXIWAY CENTERLINE
23 m(75 ft)
23 m(75 ft)
NOMINAL OFFSET 7 m(23 ft)
APPROX 8.9 m(29 ft)
FILLET R = 25.5 m(85 ft)
TURN R = 45 m(150 ft)
APPROX 10 m(33 ft)
FAA LEAD−IN FILLETL = 75 m (250 ft)
TAXIWAYCENTERLINE
NOTE: FAA GROUP V FACILITIES.
NLG PATH
WLG PATH
COCKPIT PATH
L_AC_040504_1_0010101_01_01
90˚ Turn -- Taxiway to TaxiwayJudgemental Oversteer MethodFIGURE-04-05-04-991-001-A01
04-05-04Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
APPROX 8.7 m(29 ft)
TAXIWAY CENTERLINE
30 m
(100
ft)
FILLET R = 25.5 m(85 ft)
TURN R = 51 m(167 ft)
TAXIWAYCENTERLINE
FAA LEAD−IN FILLETL = 75 m (250 ft)
30 m(100 ft) NLG PATH
WLG PATH
NOTE: FAA GROUP VI FACILITIES.L_AC_040504_1_0020101_01_01
90˚ Turn -- Taxiway to TaxiwayCockpit Tracks Centreline MethodFIGURE-04-05-04-991-002-A01
04-05-04Page 3
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
04-05-05 135˚ Turn - Taxiway to Taxiway
**ON A/C A380-800
135˚ Turn - Taxiway to Taxiway
1. This section gives the 135˚ turn - taxiway to taxiway.
04-05-05Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
23 m(75 ft)
TAXIWAY CENTERLINE
FILLET R = 25.5 m(85 ft)
APPROX 8.5 m(28 ft)
TAXIWAY CENTERLINE
23 m(75 ft)
TURN R = 45 m(150 ft)
APPROX 7 m(23 ft)
APPROX 4.9 m(16 ft)
FAA LEAD−IN FILLET
L = 75 m (250 ft)
NLG PATH
WLG PATH
COCKPIT PATH
NOTE: FAA GROUP V FACILITIES.L_AC_040505_1_0010101_01_01
135˚ Turn -- Taxiway to TaxiwayJudgemental Oversteer MethodFIGURE-04-05-05-991-001-A01
04-05-05Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
FILLET R = 25.5 m(85 ft)
APPROX 7.4 m(24 ft)
30 m(100 ft)
TURN R = 51 m(167 ft)
TAXIWAY CENTERLINE
TAXIWAY CENTERLINE
FAA LEAD−IN FILLET
L = 75 m (250 ft)
NLG PATH
WLG PATH
30 m(100 ft)
NOTE: FAA GROUP VI FACILITIES.L_AC_040505_1_0020101_01_01
135˚ Turn -- Taxiway to TaxiwayCockpit Tracks Centerline MethodFIGURE-04-05-05-991-002-A01
04-05-05Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
04-06-00 Runway Holding Bay (Apron)
**ON A/C A380-800
Runway Holding Bay (Apron)
1. This section gives the runway holding bay (Apron).
04-06-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
6.1 m(20 ft)
RUNWAY CENTERLINETAXIWAY
CENTERLINE
6.1 m(20 ft)
190 m(625 ft)
30 m(100 ft)
60 m(200 ft)
HOLDING POINT
12.2 m(40 ft)
90 m(300 ft)110 m
(360 ft)
NOTE: COORDINATE WITH USING AIRLINE FOR SPECIFIC PLANNED OPERATING PROCEDURE.
L_AC_040600_1_0010101_01_01
Runway Holding Bay (Apron)FIGURE-04-06-00-991-001-A01
04-06-00Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
04-07-00 Minimum Line-Up Distance Corrections
**ON A/C A380-800
Minimum Line-Up Distance Corrections
1. The ground manoeuvres were performed using asymmetric thrust and differential only braking toinitiate the turn.TODA: Take-Off Available DistanceASDA: Acceleration-Stop Distance Available
2. 90˚ Turn on Runway EntryThis section gives the minimum line-up distance correction for a 90˚ turn on runway entry.This manoeuvre consists in a 90˚ turn at minimum turn radius starting with the edge of the WLG ata distance of 4.5 m (15 ft) from taxiway edge, and finishing with the aircraft aligned on thecenterline of the runway, see FIGURE 4-7-0-991-003-A.During the turn, all the clearances must meet the minimum value of 4.5 m (15 ft) for this category ofaircraft as recommended in ICAO Annex 14.
3. 180˚ Turn on Runway Turn PadThis section gives the minimum line-up distance correction for a 180˚ turn on runway turn pad.This manoeuvre consists in a 180˚ turn at minimum turn radius on a standard ICAO runway turnpad geometry, .It starts with the edge of the WLG at 4.5 m (15 ft) from pavement edge, and it finishes with theaircraft aligned on the centerline of the runway, see FIGURE 4-7-0-991-004-A.During the turn, all the clearances must meet the minimum value of 4.5 m (15 ft) for this category ofaircraft as recommended in ICAO Annex 14.
4. 180˚ Turn on Runway WidthThis section gives the minimum line-up distance correction for a 180˚ turn on runway width.For this manoeuvre, the pavement width is considered to be the runway width, which is a frozenparameter (45 m (150 ft) and 60 m (200 ft)).As per the ”180˚ turn on runway” standard operating procedures described in the Flight CrewOperating Manual, the aircraft is initially angled with respect to runway centerline when starting the180˚ turn, see FIGURE 4-7-0-991-005-A.During the turn, all the clearances must meet the minimum value of 4.5 m (15 ft) for this category ofaircraft as recommended in ICAO Annex 14.
04-07-00Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
> 4.5 m(15 ft)
90° TURN ON RUNWAY ENTRY
AIRCRAFTTYPE
MAXSTEERING
ANGLE
(STANDARD WIDTH)
MINIMUM LINE−UPDISTANCE CORRECTION
ON TODA ON ASDA ON TODA ON ASDA
MINIMUM LINE−UPDISTANCE CORRECTION
70°A380−800 94 ft28.6 m 192 ft58.5 m 75 ft22.8 m 173 ft52.7 m
TAXIWAYCENTERLINE
ASDA
4.5 m(15 ft)
TODA
RUNWAY CENTERLINE
45 m (150 ft) WIDE RUNWAY60 m (200 ft) WIDE RUNWAY
NOTE:
ASDA: ACCELERATION−STOP DISTANCE AVAILABLETODA: TAKE−OFF DISTANCE AVAILABLE
L_AC_040700_1_0030101_01_00
Minimum Line-Up Distance Corrections90˚ Turn on Runway Entry
FIGURE-04-07-00-991-003-A01
04-07-00Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
180° TURN ON RUNWAY TURNPAD
AIRCRAFTTYPE
STEERINGANGLE
MAX(STANDARD WIDTH)
DISTANCECORRECTION
MINIMUM LINE−UP
70°A380−800224 ft68.1 m
TODA
ASDA
MINIMUM PAVEMENT WIDTH
ON TODA130 ft39.5 m
ON ASDA227 ft69.3 m
PAVEMENTWIDTH
MINIMUMREQUIRED
DISTANCECORRECTION
MINIMUM LINE−UP
209.9 ft64 mON TODA
122 ft37.1 mON ASDA
219 ft66.9 m
PAVEMENTWIDTH
MINIMUMREQUIRED
RUNWAY CENTERLINE
NOTE:
ASDA: ACCELERATION−STOP DISTANCE AVAILABLETODA: TAKE−OFF DISTANCE AVAILABLE
45 m (150 ft) WIDE RUNWAY 60 m (200 ft) WIDE RUNWAY
4.5 m(15 ft)
4.5 m(15 ft)> 4.5 m
(15 ft)
L_AC_040700_1_0040101_01_00
Minimum Line-Up Distance Corrections180˚ Turn on Runway Turn PadFIGURE-04-07-00-991-004-A01
04-07-00Page 3
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
180° TURN ON RUNWAY WIDTH
AIRCRAFTTYPE
MAXSTEERING
ANGLE
(STANDARD WIDTH)
MINIMUM LINE−UPDISTANCE CORRECTION
ON TODA ON ASDA ON TODA ON ASDA
MINIMUM LINE−UPDISTANCE CORRECTION
70°A380−800 NOT POSSIBLE NOT POSSIBLE
ASDA
>4.5 m(15 ft)
4.5 m(15 ft)
TODA
NOTE:
IN THE A380 FCOM, THERE IS AN OPERATIONAL PROCEDURE THAT DESCRIBES HOW TO PERFORM A 180°TURN ON A 60 m (200 ft) RUNWAY WIDTH, BUT THE RECOMMENDED 4.5 m (15 ft) MARGINS CANNOT BE MET.
4.5 m(15 ft)
RUNWAY CENTERLINE
45 m (150 ft) WIDE RUNWAY60 m (200 ft) WIDE RUNWAY
ASDA: ACCELERATION−STOP DISTANCE AVAILABLETODA: TAKE−OFF DISTANCE AVAILABLE
15°
L_AC_040700_1_0050101_01_00
Minimum Line-Up Distance Corrections180˚ Turn on Runway WidthFIGURE-04-07-00-991-005-A01
04-07-00Page 4
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
04-08-00 Aircraft Mooring
**ON A/C A380-800
Aircraft Mooring
1. This section provides information on aircraft mooring.
04-08-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
A
FWD
SLING
TOWING FITTING
MOVABLE PIN
LOCKING SCREW
HOOK
HOOK PIN
MOORING POINT
A
L_AC_040800_1_0010101_01_00
Aircraft MooringFIGURE-04-08-00-991-001-A01
04-08-00Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
TERMINAL SERVICING
05-00-00 TERMINAL SERVICING
**ON A/C A380-800
Introduction
1. Terminal servicing
This chapter provides typical ramp layouts, corresponding minimum turn round time estimations,locations of ground service points and service requirements.The information given in this chapter reflects ideal conditions. Actual ramp layouts and servicerequirements may vary according to local regulations, airline procedures and the aircraft conditions.
Section 5.1 shows typical ramp layouts for passenger aircraft at the gate or on an open apron.
Section 5.2.1 shows the minimum turn round schedule for full servicing arrangements (turn roundstations).
Section 5.2.2 shows the minimum turn round schedule for minimum servicing arrangements (en routestations).
Section 5.3 shows the minimum turn round schedule for full servicing arrangements for the freighter.
Section 5.4 gives the locations of ground service connections, the standard of connections used andtypical capacities and requirements.
Section 5.5 provides the engine starting pneumatic requirements for different engine types anddifferent ambient temperatures.
Section 5.6 provides the air conditioning requirements for heating and cooling (pull-down and pull-up)using ground conditioned air for different ambient temperatures.
Section 5.7 provides the air conditioning requirements for heating and cooling to maintain a constantcabin air temperature using low pressure conditioned air.
Section 5.8 shows the ground towing requirements taking into account different ground surface andaircraft conditions.
05-00-00Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-01-00 Aircraft Servicing Arrangements
**ON A/C A380-800
Airplane Servicing Arrangements
1. This section provides typical ramp layouts, showing the various GSE items in position during typicalturn--round scenarios.
These ramp layouts show typical arrangements only. Each operator will have its own specificrequirements/regulations for the positioning and operation on the ramp.
GROUND SUPPORT EQUIPMENT
AC AIR CONDITIONING UNITAS AIR START UNIT
BULK BULK TRAINCAT CATERING TRUCK
CB CONVEYOR BELTCLEAN CLEANING TRUCK
FUEL FUEL HYDRANT DISPENSER OR TANKERGPU GROUND POWER UNIT
LDCL LOWER DECK CARGO LOADERLV LAVATORY VEHICLE
PBB PASSENGER BOARDING BRIDGEPS PASSENGER STAIRS
TOW TOW TRACTORUDCAT UPPER DECK CATERING TRUCK
ULD ULD TRAINWV POTABLE WATER VEHICLE
05-01-00Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-01-01 Typical Ramp Layout (Open Apron)
**ON A/C A380-800
Typical Ramp Layout (Open Apron)
1. This section gives the typical ramp layout (Open Apron).The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m (24.61 ft) fromthe aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears).
05-01-01Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
CAT
LD CL
GPU
GPU
ULD
BULK
TOW
METERS
FEET16 320
0 5 10 15
48
LD CL
CLEAN
STAND SAFETY LINE
CB
FUEL
AS
CAT
AC
PS
PS
PS
CATLV
UDCAT
WV
ULD
L_AC_050101_1_0010101_01_02
Typical Ramp LayoutOpen Apron
FIGURE-05-01-01-991-001-A01
05-01-01Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-01-02 Typical Ramp Layout (Gate)
**ON A/C A380-800
Typical Ramp Layout (Gate)
1. This section gives the baseline ramp layout (Gate).The Stand Safety Line delimits the Aircraft Safety Area (minimum distance of 7.5 m (24.61 ft) fromthe aircraft). No vehicle must be parked in this area before complete stop of the aircraft (wheelchocks in position on landing gears).
05-01-02Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
GPU
GPU
LD CL
ULD
BULK
LD CL
CLEAN
CB
AS
CAT
CAT
AC
FUELFUEL
PBB
PBB
CAT LV
UDCAT
WV
ULD
STAND SAFETY LINE
METERS
FEET16 320
0 5 10 15
48 TOW
L_AC_050102_1_0010101_01_02
Typical Ramp LayoutGate
FIGURE-05-01-02-991-001-A01
05-01-02Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-02-01 Typical Turn-Round Time - Standard Servicing Via Main Deck and Upper Deck
**ON A/C A380-800
Typical Turn-Round Time - Standard Servicing Via Main Deck and Upper Deck
1. This section provides a typical turn-round time chart showing the typical time for ramp activitiesduring aircraft turn-round.Actual times may vary due to each operator’s specific practice, resources, equipment and operatingconditions.
2. Assumptions used for standard servicing via main and upper deck during typical turn-round time
A. PASSENGER HANDLING555 pax (22 F/C + 96 B/C +/ 437 YC)All passengers deboard and board the aircraft2 Passenger Boarding Bridges (PBB) used at doors M2L and U1LEquipment positioning/removal main deck + opening/closing door = +3 min.Equipment positioning/removal upper deck + opening/closing door = +4 min.No Passenger with Reduced Mobility (PRM) on board
Deboarding:- 356 pax at door M2L (22 F/C + 334 Y/C)- 199 pax at door U1L (96 B/C + 103 Y/C)- Deboarding rate = 25 pax/min per door- Priority deboarding for premium passengers
Boarding:- 356 pax at door M2L (22 F/C + 334 Y/C)- 199 pax at door U1L (96 B/C + 103 Y/C)- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +4 min.
B. CARGO2 cargo loaders + 1 belt loaderEquipment positioning/removal + opening/closing door = +2.5 min.
C. REFUELLING242 700 l (64 115 US gal) at 40 psigDispenser positioning/removal = +8 min.
D. CLEANINGCleaning is performed in available time
E. CATERING3 main deck catering trucks + 1 upper deck catering truckMain deck equipment positioning + door opening = +5 min.Main deck closing door + equipment removal = 3 min.Upper deck equipment positioning + door opening = +9 min.Upper deck closing door + equipment removal = 4 min.
Full Size Trolley Equivalent (FSTE) to unload and load: 78 FSTE- 28 FSTE at door M2R- 16 FSTE at door M4R- 23 FSTE at door U1R- 11 FSTE at door M5LTime for trolley exchange = 1.5 min per FSTETime for trolley exchange via lift = 2 min per FSTE
F. GROUND HANDLING/SERVICINGStart of operations:- Bridges/stairs: t0 = 0- Other equipment: t = t0 + 1 min.
Ground Power Unit (GPU): up to 4 x 90 kVAAir conditioning: up to 4 hosesPotable water servicing: 100% uplift, 1 700 l (449 US gal) at 60 l/min (15.85 US gal/min)Toilet servicing: draining + rinsing
05-02-01Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
GSE POSITIONING/REMOVAL
ACTIVITY
CRITICAL PATH
AT M2LDEBOARDING/BOARDING
HEADCOUNTING & LPS
CATERING AT M4R
CLEANING AT M1R
CARGO FWD CC
BULK
REFUELLING
POTABLE WATER SERVICING
TOILET SERVICING
DEBOARDING/BOARDINGAT U1L
CATERING AT U1R
CATERING AT M5L
CARGO AFT CC
CATERING AT M2R
100 20 30 40 50 60 70 80 90
TRT: 90 min
AVAILABLE TIME
L_AC_050201_1_0020101_01_02
Typical Turn-Round TimeServicing Via Main and Upper Deck
FIGURE-05-02-01-991-002-A01
05-02-01Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-02-02 Typical Turn-Round Time - Servicing Via Main Deck
**ON A/C A380-800
Typical Turn-Round Time - Servicing Via Main Deck
1. This section provides a typical turn-round time chart showing the typical time for ramp activitiesduring aircraft turn-round.Actual times may vary due to each operator’s specific practice, resources, equipment and operatingconditions.
2. Assumptions used for standard servicing via main deck only during typical turn-round time
A. PASSENGER HANDLING555 pax (22 F/C + 96 B/C + 437 Y/C)All passengers deboard and board the aircraft2 Passenger Boarding Bridges (PBB) used at doors M1L and M2LEquipment positioning/removal main deck + opening/closing door = +3 min.No Passenger with Reduced Mobility (PRM) on board
Deboarding:- 221 pax at door M1L (22 F/C + 96 B/C + 103 Y/C)- 334 pax at door M2L (334 Y/C)- Deboarding rate = 25 pax/min per door- Priority deboarding for premium passengers
Boarding:- 221 pax at door M1L (22 F/C + 96 B/C + 103 Y/C)- 334 pax at door M2L (334 Y/C)- Boarding rate = 15 pax/min per door- Last Pax Seating allowance (LPS) + headcounting = +4 min.
B. CARGO2 cargo loaders + 1 belt loaderEquipment positioning/removal + opening/closing door = +2.5 min.
C. REFUELLING242 700 l (64 115 US gal) at 40 psigDispenser positioning/removal = +8 min.
D. CLEANINGCleaning is performed in available time
E. CATERING3 main deck catering trucksMain deck equipment positioning + door opening = +5 min.Main deck closing door + equipment removal = 3 min.Full Size Trolley Equivalent (FSTE) to unload and load: 78 FSTE- 28 FSTE at door M2R- 16 FSTE at door M4R- 23 FSTE at door U1R- 11 FSTE at door M5LTime for trolley exchange = 1.5 min per FSTETime for trolley exchange via lift = 2 min per FSTE
F. GROUND HANDLING/SERVICINGStart of operations:- Bridges/stairs: t0 = 0- Other equipment: t = t0 + 1 min.
Ground Power Unit (GPU): up to 4 x 90 kVAAir conditioning: up to 4 hosesPotable water servicing: 100% uplift, 1 700 l (449 US gal) at 60 l/min (15.85 US gal/min)Toilet servicing: draining + rinsing
05-02-02Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
AT M1LDEBOARDING/BOARDING
HEADCOUNTING & LPS
CATERING AT M4R
CLEANING AT M1R
CARGO FWD CC
BULK
REFUELLING
POTABLE WATER SERVICING
TOILET SERVICING
DEBOARDING/BOARDINGAT M2L
CATERING AT M5L
CARGO AFT CC
CATERING AT M2R
20
GSE POSITIONING/REMOVAL
ACTIVITY
CRITICAL PATH
0 40 60 80 100 120 140
TRT: 140 min
AVAILABLE TIME
L_AC_050202_1_0010101_01_02
Typical Turn-Round TimeServicing Via Main Deck
FIGURE-05-02-02-991-001-A01
05-02-02Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-04-01 Ground Service Connections Layout
**ON A/C A380-800
Ground Service Connections Layout
1. This section gives the ground service connections layout.
05-04-01Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
1 − GROUNDING POINT NLG2 − GROUND ELECTRICAL POWER CONNECTORS3 − POTABLE WATER DRAIN PANEL4 − OXYGEN SYSTEM
6 − HIGH PRESSURE AIR ENGINE START7 − VFG AND STARTER OIL FILLING8 − ENGINE OIL FILLING*9 − HYDRAULIC RESERVOIR SERVICING PANEL10 − YELLOW HYDRAULIC GROUND CONNECTOR
5 − LOW PRESSURE PRECONDITIONED AIR
13 − GROUNDING POINT WLG14 − GROUNDING POINT BLG
16 − OVERPRESSURE PROTECTOR17 − REFUEL/DEFUEL CONTROL PANEL18 − POTABLE WATER SERVICE PANEL
15 − NACA FLAME ARRESTOR
11 − GREEN HYDRAULIC GROUND CONNECTOR12 − PRESSURE REFUEL CONNECTORS
19 − TOILET AND WASTE SERVICE PANEL20 − APU OIL FILLING
1
34
15
12
1119
20
8 712
10
15
6
5
1718
2
13
14
9
8 7
8
7
87
16
16
15
16
NOTE:
*FOR THE GP 7200 ENGINE, THE ENGINE OIL SERVICING POINTS (8) ARE LOCATED SYMMETRICALLYON THE LH SIDE OF EACH ENGINE.
THE ENGINE OIL SERVICING POINTS (8) ARE SHOWN FOR THE RR TRENT 900 ENGINE.
L_AC_050401_1_0010101_01_03
Ground Service Connections LayoutFIGURE-05-04-01-991-001-A01
05-04-01Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-04-02 Grounding Points
**ON A/C A380-800
Grounding Points
1. Grounding Points
DISTANCE: Meters (ft)
AFT OF NOSEFROM AIRPLANECENTERLINE
MEAN HEIGHT FROMGROUND
On Nose Landing Gear 5.713 (18.7) 0.182 (0.6) On the RHside
1.385 (4.5)
On left Wing Gear leg 34.207 (112.2) 5.949 (19.5) 1.237 (4.0)
On right Wing Gear leg 34.207 (112.2) 5.949 (19.5) 1.237 (4.0)
On left Body Gear leg(Outboard)
37.158 (121.9) 2.852 (9.4) 1.379 (4.5)
On left Body Gear leg(Inboard)
37.158 (121.9) 2.412 (7.9) 1.379 (4.5)
On right Body Gear leg(Outboard)
37.158 (121.9) 2.852 (9.4) 1.379 (4.5)
On right Body Gear leg(Inboard)
37.158 (121.9) 2.412 (7.9) 1.379 (4.5)
A. The grounding stud on each landing gear is designed for use with a clip-on connector, such asan Appleton TGR.
B. The grounding studs are used to connect the airplane to approved ground connection on theramp or in the hangar for:
(1) refuel/defuel operations
(2) maintenance operations
(3) bad weather conditions.
05-04-02Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
A
A
GROUNDPOINT
L_AC_050402_1_0010101_01_00
Ground Points NLGFIGURE-05-04-02-991-001-A01
05-04-02Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
GROUND POINT A
A
L_AC_050402_1_0020101_01_00
Ground Point WLGFIGURE-05-04-02-991-002-A01
05-04-02Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
GROUNDPOINTS
(RIGHT ONE SHOWN LEFT ONE SIMILAR)
A
A
L_AC_050402_1_0030101_01_00
Ground Points BLGFIGURE-05-04-02-991-003-A01
05-04-02Page 4
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-04-03 Hydraulic System
**ON A/C A380-800
Hydraulic System
1. Door Location
DISTANCE: Meters (ft)
FROM AIRCRAFTCENTERLINE
AFT OFNOSE
RH SIDE LH SIDE
MEAN HEIGHTFROM GROUND
-- Green Hydraulic Ground Connectors:(Access door 469FL)
34.67(113.75)
14.90 (48.88) 5.08 (16.67)
-- Yellow Hydraulic Ground Connectors:(Access door 479FL)
34.67(113.75)
14.90(48.88)
5.08 (16.67)
-- Hydraulic Reservoir Servicing Panel:(Access door 197CB)
31.89(104.63)
2.34 (7.68) 1.71 (5.61)
A. Reservoir Pressurization
(1) One connector ISO 4570.
B. Reservoir Filling
(1) One connector AE96993E, 1/4 in.
05-04-03Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
A
B
RESERVOIRPRESSURIZATION
CONNECTOR
RESERVOIR FILLINGCONNECTOR
Z190
A
B
L_AC_050403_1_0010101_01_00
Ground Service ConnectionsHydraulic Reservoir Servicing Panel
FIGURE-05-04-03-991-001-A01
05-04-03Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
Z460
Z470 B C
A
SELF SEALINGGND CONNECTOR
GREEN HP
SELF SEALINGGND CONNECTOR
GREEN SUCTION
SELF SEALINGGND CONNECTOR
YELLOW HP
SELF SEALINGGND CONNECTOR
YELLOW SUCTION
B C
A
FOR LH PYLON FOR RH PYLON
A
L_AC_050403_1_0020101_01_00
Ground Service ConnectionsHydraulic Ground ConnectionsFIGURE-05-04-03-991-002-A01
05-04-03Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-04-04 Electrical System
**ON A/C A380-800
Electrical System
1. AC External Power
DISTANCEFROM AIRCRAFT CENTERLINE
ACCESSAFT OF NOSE
RH SIDE LH SIDE
MEAN HEIGHTFROM
GROUNDRight Side Access Door:134AR
5.99 m(19.65 ft)
0.45 m(1.48 ft)
-2.59 m(8.5 ft)
Left Side Access Door:133AL
5.99 m(19.65 ft)
- 0.45 m(1.48 ft)
2.59 m(8.5 ft)
A. External Power Receptacles:
(1) Four standard ISO 461 Style 3 - 90 kVA each.
B. Power Supply:
(1) Three-phase, 115V, 400 Hz.
C. Electrical Connectors:
(1) AC outlets: HUBBELL 5258
(2) DC outlets: HUBBELL 7472.
D. Electrical Loads on Ground:For detailed information, refer to SIL 24-076.
NOTE : ”Default Loads” are the basic loads that are supplied when the electrical powersystem is activated (avionics fan, etc.).
NOTE : This paragraph gives examples based on typical configuration. The values may varydepending on aircraft configuration.
(1) Ground Service Network:When only the Ground Service Network is activated, only the electrical loads for cargoloading, cleaning, servicing and main cabin lighting are available.One 90 kVA GPU is necessary.
(4) Hangar Maintenance:The most consuming configuration is a full check of the flight controls with the fourElectrical Motor Pumps (EMP) switched ON.- Default loads: 53 kVA- Cabin fans: 35 kVA- Lights: 23.5 kVA- EHA/EBHA: 24 kVA- EMP (x4): 92 kVATotal loads: 227.5 kVAFour 90 kVA GPU are necessary.
2. AC Emergency Generation
DISTANCEFROM AIRCRAFT CENTERLINE
ACCESSAFT OF NOSE
RH SIDE LH SIDE
MEAN HEIGHTFROM
GROUNDRAT Safety-Pin
InstallationAccess Panel: 531DL
31 m(101.71 ft)
-9.5 m
(31.17 ft)3.2 m
(10.5 ft)
The AC Emergency Generation System supplies 115VAC electrical power to the emergency bus bar ifan electrical emergency occurs. There is an electrical emergency when:- A Loss of Main Electrical System (LMES) signal occurs- A Total Engine Flame-Out (TEFO) signal occurs.
05-04-04Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
When the system operates, a Ram Air Turbine (RAT-ELEC) module extends from the flap-track 2fairing of the left wing into the airflow. The turbine supplies power to a generator throughmechanical transmission. The system includes an Emergency Generator Control-Unit (GCU-ELECRAT) that controls and monitors generator operation. The system can operate automatically ormanually.A safety pin is used to prevent unwanted extension of the RAT during servicing or maintenancetasks.The pin is engaged in the RAT uplock assembly through the RAT fairing hand hole when the RAT isretracted.
05-04-04Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
RECEPTACLES
A
B
FWD
FWD
FR17FR18
FR17 FR18
FR17 FR18EXTERNAL POWER
RECEPTACLESEXTERNAL POWER
133AL134AR
A
B
L_AC_050404_1_0010101_01_01
Ground Service ConnectionsElectrical Service Panel
FIGURE-05-04-04-991-001-A01
05-04-04Page 4
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
Z531
A
531DL
B
A
B
C
C
NOTE:ALWAYS KEEP THE WARNING FLAGOUT OF THE RAT FAIRING HAND HOLE.
RAM AIR TURBINE (RAT)
RAT UPLOCK SAFETY−PIN
L_AC_050404_1_0050101_01_00
Ground Service ConnectionsRam Air Turbine retracted
FIGURE-05-04-04-991-005-A01
05-04-04Page 5
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
RAM AIR TURBINE (RAT)
A
531KR
531KL
(5.41 ft)1.65 m
B
GROUND
B
FWD
Z531
A
L_AC_050404_1_0060101_01_00
Ground Service ConnectionsRam Air Turbine extended
FIGURE-05-04-04-991-006-A01
05-04-04Page 6
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-04-05 Oxygen System
**ON A/C A380-800
Oxygen System
1. Oxygen System
DISTANCEFROM AIRCRAFT
CENTERLINEACCESSAFT OF NOSE
RH SIDE LH SIDE
MEANHEIGHTFROM
GROUNDAccess Panels: 132AJW
132EJW
13.32 m(43.70 ft)
2.23 m(7.32 ft)
-3.25 m(10.66 ft)
Zero, one or two service connections (external charging in the FWD Cargo compartment) MS22066Std.
05-04-05Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
FR29
A
B
FR34
FR17
FR29
Z130
PASSENGEROXYGENFILLING POINT
CREW OXYGENFILLING POINT
L_AC_050405_1_0020101_01_00
A
B
Ground Service ConnectionsOxygen System
FIGURE-05-04-05-991-002-A01
05-04-05Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-04-06 Fuel System
**ON A/C A380-800
Fuel System
1. Refuel/Defuel Control Panel
DISTANCEFROM AIRCRAFT CENTERLINE
AFT OF NOSERH SIDE LH SIDE
MEAN HEIGHTFROM GROUND
Refuel/Defuel ControlPanel: (Access Door199KB)
48 m(157.48 ft)
0.68 m(2.23 ft)
-1.98 m(6.50 ft)
2. Refuel/Defuel Connectors
DISTANCEFROM AIRCRAFT CENTERLINE
AFT OF NOSERH SIDE LH SIDE
MEAN HEIGHTFROM GROUND
Refuel/Defuel Coupling,Left: (Access Door 522GB)
31.89 m(104.63 ft)
-17.97 m(58.96 ft)
5.94 m(19.49 ft)
Refuel/Defuel Coupling,Right: (Access Door622 GB)
31.89 m(104.63 ft)
17.97 m(58.96 ft)
-5.94 m
(19.49 ft)
A. Refuel/Defuel couplings:
(1) Four standard 2.5 in. ISO 45 connections.
B. Refuel pressure:
(1) Maximum pressure: 50 psi (3.45 bar).
3. Overpressure Protector and NACA Flame Arrestor
DISTANCEFROM AIRCRAFT CENTERLINE
AFT OF NOSERH SIDE LH SIDE
MEAN HEIGHTFROM GROUND
Overpressure Protector 46.65 m(153.05 ft)
36.75 m(120.57 ft)
36.75 m(120.57 ft)
7.51 m(24.64 ft)
NACA Flame Arrestor 46.33 m(152.00 ft)
35.98 m(118.04 ft)
35.98 m(118.04 ft)
7.44 m(24.41 ft)
05-04-06Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
Z190
HI LVL
HI LVL
APU EMERGENCY
INCREASE
DECREASE
PRESELECT
PRESELECT (PFQ)
OVERFLOWFAULT
SHUTOFFTEST
NORMAL
BATTERY
POWER SUPPLY
ACTUAL (FOB)
STATUS
MANREFUEL
XFR
DEFUEL
AUTOREFUEL
OFF
MODE SELECT
FEED 1
FEED 1
L OUTR
L OUTR
R MID
OPEN
SHUT
R MID
R INR
R INR
TRIM
TRIM
L INR
L INR
L MID
L MID
R OUTROPEN
SHUT
R OUTR
FEED 4
FEED 4
FEED 3
FEED 3
FEED 2
FEED 2
SHUTDOWN
REFUEL/DEFUEL VALVES
kg
B
42QU
BA
A
L_AC_050406_1_0010101_01_00
Ground Service ConnectionsRefuel/Defuel Control Panel
FIGURE-05-04-06-991-001-A01
05-04-06Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
REFUEL PRESSURE
REFUEL / DEFUEL COUPLINGS
Z500
Z600 ALH SIDE SHOWN
RH SIDE SYMETRICAL
B
B
A
A
L_AC_050406_1_0020101_01_00
Ground Service ConnectionsPressure Refuel Connections
FIGURE-05-04-06-991-002-A01
05-04-06Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
L_AC_050406_1_0030101_01_01
550CB(650CB)
COVERPRESSURE PROTECTOR
A
NACA FLAME ARRESTOR
B
550BB(650BB)
A
B
C
A FWD
LH SIDE SHOWNRH SIDE SYMMETRICAL
Ground Service ConnectionsOverpressure Protector and NACA Flame Arrestor
FIGURE-05-04-06-991-003-A01
05-04-06Page 4
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-04-07 Pneumatic System
**ON A/C A380-800
Pneumatic System
1. Low Pressure Connectors
DISTANCE : Meters (ft)
FROM AIRPLANE CENTERLINEAFT OF NOSE R SIDE L SIDE MEAN HEIGHT
FROM GROUNDaccess doors 191GB 21.85 (71.69) 1.24 (4.07) 2.08 (6.82)
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
LOW PRESSURE AIR CONNECTOR
Z190
BB
B
BA
A
B
L_AC_050407_1_0010101_01_00
Ground Service ConnectionsLow Pressure Preconditioned AirFIGURE-05-04-07-991-001-A01
05-04-07Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
HIGH PRESSURE AIR CONNECTORS
Z190
BA
A
B
L_AC_050407_1_0020101_01_00
Ground Service ConnectionsHigh Pressure Preconditioned AirFIGURE-05-04-07-991-002-A01
05-04-07Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-04-08 Potable Water System
**ON A/C A380-800
Potable Water System
1. Potable Water SystemThis section gives data related to the location of the ground service connections.
DISTANCE: Meters (ft)
FROM AIRCRAFTCENTERLINE
AFT OF NOSELH Side RH Side
MEANHEIGHTFROM
GROUND
Potable water ground service panel:access door 199NB
43.67(143.27)
0.37(1.21)
2.13(6.99)
Potable water drain panel:access door 133BL
9.83(32.25)
0.3(0.98)
2.74(8.99)
NOTE : Distances are approximate.
A. Connections
Fill and drain port - ISO 17775, 3/4 in.
B. Capacity :
(1) Total Capacity- Standard configuration (six tanks): 1700 l (449 US gal).- Optional configuration (seven tanks): 1998 l (528 US gal).- Optional configuration (eight tanks): 2267 l (599 US gal).
C. Filling pressure :
(1) Max Filling Pressure: 8.6 bar (125 psi).
05-04-08Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
80LWL PRE
1000
0/
PRESS UP OR DOWN TO PRESET
0
50
DOWN PRESET WATER UP
MENUSELECT
DRAIN FILL
NORMAL
FILL/DRAIN PORT
Z190
BA
A
BL_AC_050408_1_0010101_01_01
Ground Service ConnectionsPotable Water Ground Service Panel
FIGURE-05-04-08-991-001-A01
05-04-08Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
ACCESS DOOR
DRAIN PORT
FWD CARGOFWD CARGOCOMPARTMENTDOOR
DRAIN VALVECONTROL HANDLE
A
B
A
Z130
FR23
BFR24
L_AC_050408_1_0040101_01_01
Ground Service ConnectionsPotable Water Drain Panel
FIGURE-05-04-08-991-004-A01
05-04-08Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
FR59
FR57
FR55
A
OPTIONAL
OPTIONAL
Z140
POTABLE WATER TANKS(STANDARD: 6 TANKS,OPTION: 7 OR 8 TANKS)
A
L_AC_050408_1_0050101_01_01
Ground Service ConnectionsPotable Water Tanks LocationFIGURE-05-04-08-991-005-A01
05-04-08Page 4
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-04-09 Oil System
**ON A/C A380-800
Engine Oil Servicing
1. Engine Oil Servicing (TRENT900 Engines)
DISTANCE : Meters (ft)
FROM AIRPLANECENTERLINE
AFT OF NOSER SIDE L SIDE
MEANHEIGHTFROM
GROUND
-- Engine 1 (access door 416BR) 32.65 (107.12)23.58
(77.36)4.24 (13.91)
-- Engine 2 (access door 426BR) 24.98 (81.96)12.74
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
Z310
FULL MARK
VISUAL SIGHT−GLASS
FILL CAP
B
A
FWD
FR117
FR112C
B
A
C
L_AC_050409_1_0150101_01_00
Ground Service ConnectionsAPU Oil Servicing
FIGURE-05-04-09-991-015-A01
05-04-09Page 11
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-04-10 Vacuum Toilet System
**ON A/C A380-800
Vacuum Toilet System
1. AccessThis section gives data related to the location of the ground service connections.
2. Technical specifications
DISTANCES: Meters (ft)
FROM AIRCRAFT CENTERLINEAFT OF NOSE
LH Side RH SideMEAN HEIGHTFROM GROUND
Waste Water GroundService Panel Accessdoor 171AL
53.31(174.90)
0.26(0.85)
3.40(11.15)
NOTE : Distances are approximate.
A. Connectors
(1) Toilet waste drain-connection - ISO 17775, 4 in.
(2) Toilet rinse/fill port - ISO 17775, 1 in.
B. CapacityThere are four waste tanks, two upper deck tanks and two main deck tanks, see FIGURE5-4-10-991-003-A.
(1) Upper Deck Waste-Tanks- 373 l (99 US gal).Each tank is precharged with 35 l (9 US gal) of chemical fluid.
(2) Main Deck Waste-Tanks- 675 l (178 US gal).Each tank is precharged with 35 l (9 US gal) of chemical fluid.
(3) Total Waste Tank Capacity- 2096 l (554 US gal).
C. PressureMaximum pressure for rinsing and precharge to the rinse/fill port is 3.45 bar (50 psi).
05-04-10Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
WASTE TANK DRAIN VALVEOPEN
UPPERDECK
MAINDECK
RH LH RH LH
CLOSE
CONTROLLEVER
CONNECTIONWASTE DRAIN
FILL AND RINSECONNECTION
FWDB
Z160
FR86FR91A
A
B
L_AC_050410_1_0010101_01_00
Ground Service ConnectionsVacuum Toilet System
FIGURE-05-04-10-991-001-A01
05-04-10Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
Z170
A
FR91
FR92
FR93
FR94
FR95
A
WASTE TANK(STANDARD: 4 TANKS)
L_AC_050410_1_0030101_01_01
Ground Service ConnectionsWaste Tanks Location
FIGURE-05-04-10-991-003-A01
05-04-10Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-05-00 Engine Starting Pneumatic Requirements
**ON A/C A380-800
Engine Starting Pneumatic Requirements
1. The purpose of this section is to provide the air data at the aircraft connection, needed to start theengine within no more than 90 seconds, at sea level (0 ft), for a set of Outside Air Temperatures(OAT).
ABBREVIATION DEFINITION
A/C Aircraft
ASU Air Start UnitHPGC High Pressure Ground Connection
OAT Outside Air Temperature
A. Air data (discharge temperature, absolute discharge pressure) are given at the HPGC.
B. For the requirements below, the configuration with two HPGC is used. Using more than twoconnectors (for a given mass flow rate and discharge pressure from the ASU) will lower thepressure loss in the ducts of the bleed system and therefore increase the performances at theengine starter.
C. For a given OAT the following charts are used to determine an acceptable combination for airdata: discharge temperature, absolute discharge pressure and mass flow rate at the HPGC.
D. This section addresses requirements for the ASU only, and is not representative of the startperformance of the aircraft using the APU or engine cross bleed procedure.
E. To protect the A/C, the charts feature, if necessary:- The maximum discharge pressure at the HPGC- The maximum discharge temperature at the HPGC.
05-05-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
EXAMPLE:FOR AN OAT OF 15° C (59° F) AND AN ASU PROVIDING A DISCHARGE TEMPERATURE OF 135° C (275° F)
− THE REQUIRED PRESSURE AT HPGC IS 42.8 psia− THE REQUIRED AIRFLOW AT A/C CONNECTION IS 96 kg/min.
AT HPGC:
IN CASE THE ACTUAL DISCHARGE TEMPERATURE OF THE ASU DIFFERS SUBSTANTIALLY FROM THEONES GIVEN IN THE CHARTS, A SIMPLE INTERPOLATION (LINEAR) IS SUFFICIENT TO DETERMINE THE
FOR AN OAT OF 15° C (59° F) AND AN ASU PROVIDING A DISCHARGE TEMPERATURE OF 195° C (383° F)AT HPGC, INTERPOLATING BETWEEN THE LINES 135° C (275° F) AND 265° C (509° F) RESULTS IN:− A REQUIRED PRESSURE AT HPGC OF 41.8 psia− A REQUIRED AIRFLOW AT A/C CONNECTION OF 88 kg/min.
REQUIRED AIR DATA.
EXAMPLE:
NOTE:
ENGINE ALLIANCE GP 7200/SEA LEVELSTARTING TIME: LESS THAN 90 s
AIR DATA AT AIRCRAFT CONNECTION (TWO CONNECTORS)140
130
120
110
100
90
80
70
60
58
56
54
52
50
48
46
44
42
40
0 20 40 60 80 100 120OUTSIDE AIR TEMPERATURE OAT (° F)
150
170
190
210
230
250
270
5 15 25 35 45 55OUTSIDE AIR TEMPERATURE OAT (° C)
40 45 50 55ABSOLUTE PRESSURE (psia)
AIR
FLO
W (
kg/m
in)
AB
SO
LUT
E P
RE
SS
UR
E (
psia
)
AIR
FLO
W (
lb/m
in)
265° C (509° F) MAX.135° C (275° F)60° C (140° F)
ASU DISCHARGE TEMPERATURE:
−40 −20
−45 −35 −25 −15 −5
L_AC_050500_1_0030101_01_02
Example for Use of the ChartsFIGURE-05-05-00-991-003-A01
05-05-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
ENGINE ALLIANCE GP 7200/SEA LEVELSTARTING TIME: LESS THAN 90 s
AIR DATA AT AIRCRAFT CONNECTION (TWO CONNECTORS)140
130
120
110
100
90
80
70150
170
190
210
230
250
270
40 45 50 55ABSOLUTE PRESSURE (psia)
0 20 40 60 80 100 120
OUTSIDE AIR TEMPERATURE OAT (° F)
5 15 25 35 45 55OUTSIDE AIR TEMPERATURE OAT (° C)
60
58
56
54
52
50
48
46
44
42
40
AIR
FLO
W (
kg/m
in)
AB
SO
LUT
E P
RE
SS
UR
E (
psia
)
AIR
FLO
W (
lb/m
in)
265° C (509° F) MAX.135° C (275° F)60° C (140° F)
ASU DISCHARGE TEMPERATURE:
L_AC_050500_1_0040101_01_01
Engine Starting Pneumatic RequirementsEngine Alliance - GP 7200
FIGURE-05-05-00-991-004-A01
05-05-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
ROLLS ROYCE TRENT 900/SEA LEVELSTARTING TIME: LESS THAN 90 s
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-06-00 Ground Pneumatic Power Requirements
**ON A/C A380-800
Ground Pneumatic Power Requirements
1. GeneralThis section describes the required performance for the ground equipment to maintain the cabintemperature at 27 ˚C (80.6 ˚F) after boarding (Section 5.7 - steady state), and provides the timeneeded to cool down or heat up the aircraft cabin to the required temperature (Section 5.6 - dynamiccases with aircraft empty).
ABBREVIATION DEFINITION
A/C Aircraft
AHM Aircraft Handling Manual
AMM Aircraft Maintenance ManualGC Ground ConnectionGSE Ground Service Equipment
IFE In-Flight Entertainment
LPGC Low Pressure Ground ConnectionOAT Outside Air Temperature
PCA Pre-Conditioned Air
A. The air flow rates and temperature requirements for the GSE, provided in Sections 5.6 and 5.7,are given at A/C ground connection.
NOTE : The cooling capacity of the equipment (kW) is only indicative and is not sufficient byitself to ensure the performance (outlet temperature and flow rate combinations arethe requirements needed for ground power).An example of cooling capacity calculation is given in Section 5.7.
B. The air flow rates and temperature requirements for the GSE are given for the A/C in theconfiguration ”4 LP ducts connected”.
NOTE : The maximum air flow is driven by pressure limitation at LPGC.
C. For temperatures at ground connection below +2 ˚C (+35.6 ˚F) (Subfreezing), the groundequipment shall be compliant with the Airbus document ”Subfreezing PCA Carts - ComplianceDocument for Suppliers” (contact Airbus to obtain this document) defining all the requirementswith which Subfreezing Pre-Conditioning Air equipment must comply to allow its use on Airbusaircraft. These requirements are in addition to the functional specifications included in the IATAAHM997.
2. Ground Pneumatic Power RequirementsThis section provides the ground pneumatic power requirements for:
05-06-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
- Heating (pull up) the cabin, initially at OAT, up to 21 ˚C (69.8 ˚F) (see FIGURE5-6-0-991-001-A)
- Cooling (pull down) the cabin, initially at OAT, down to 27 ˚C (80.6 ˚F) (see FIGURE5-6-0-991-002-A).
05-06-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
OAT ISA −38° C (−36.4° F); GC OUTLET +70° C (+158° F); EMPTY CABIN; IFE OFF;NO SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON
20 40 60 80 100 120
3.5
4
4.5
5
5.5
6
6.5
03
MAXIMUM AIR FLOW
PULL UP PERFORMANCE
7
8
9
10
11
12
13
14
AIR
FLO
W A
T G
C (
kg/s
)
AIR
FLO
W A
T G
C (
lb/s
)
TIME TO HEAT CABIN TO +21° C (+69.8° F) ON GROUND (min)
715
L_AC_050600_1_0010101_01_00
Ground Pneumatic Power RequirementsHeating
FIGURE-05-06-00-991-001-A01
05-06-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
OAT ISA +23° C (+73.4° F); GC OUTLET −10° C (+14° F); EMPTY CABIN; IFE OFF;SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON
AIR
FLO
W A
T G
C (
kg/s
)
0 20 40 60 80 100 120
AIR
FLO
W A
T G
C (
lb/s
)
0
1
2
3
4
5
6
7PULL DOWN PERFORMANCE
TIME TO COOL CABIN TO +27° C (+80.6° F) ON GROUND (min)
MAXIMUM AIR FLOW
0
2
4
6
8
10
12
14
OAT ISA +23° C (+73.4° F); GC OUTLET +2° C (+35.6° F); EMPTY CABIN; IFE OFF;SOLAR LOAD; LIGHTS ON; RECIRCULATION FANS ON
L_AC_050600_1_0020101_01_00
Ground Pneumatic Power RequirementsCooling
FIGURE-05-06-00-991-002-A01
05-06-00Page 4
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-07-00 Preconditioned Airflow Requirements
**ON A/C A380-800
Preconditioned Airflow Requirements
1. This section provides the preconditioned airflow rate and temperature needed to maintain the cabintemperature at 27˚C (80.6˚F).
These settings are not intended to be used for operation (they are not a substitute for the settingsgiven in the AMM). They are based on theoretical simulations and give the picture of a real steadystate.For the air conditioning operation, the AMM details the procedure and the preconditioned airflowsettings to maintain the cabin temperature below 27˚C (80.6˚F) during boarding (therefore it is nota steady state).
05-07-00Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-08-00 Ground Towing Requirements
**ON A/C A380-800
Ground Towing Requirements
1. This section provides information on aircraft Towing.
The A380-800 is designed with means for conventional towing or towbarless towing. Information ontowbarless towing can be found in SIL 09-002 and chapter 9 of the Aircraft Maintenance Manual.It is possible to tow or push the aircraft, at maximum ramp weight with engines at zero or up to idlethrust, using a towbar attached to the nose gear leg. The towbar fitting is installed at the front ofthe leg (optional towing fitting for towing from the rear of the NLG available).The body gears have attachment points for towing or debogging (for details refer to chapter 7 of theAircraft Recovery Manual).
NOTE : Information on aircraft towing procedures and corresponding aircraft limitations are given inchapter 9 of the Aircraft Maintenance Manual.
Ground Towing Requirements A380-800 Models shows the chart to determine the towbar pull andtow tractor mass requirements as function of the following physical characteristics, see FIGURE5-8-0-991-001-A:- Aircraft weight,- Slope,- Number of engines at idle.The chart is based on the A380-800 engine type with the highest idle thrust. The chart is thereforevalid for all A380-800 models.
2. Towbar design guidelines
The aircraft towbar shall respect the following norms:- SAE AS 1614, ”Main Line Aircraft TowBar Attach Fitting Interface”,- SAE ARP1915, ”Aircraft TowBar”,- ISO 8267-1, ”Aircraft - Towbar attachment fitting - Interface requirements - Part 1: Main line
aircraft”,- ISO 9667, ”Aircraft ground support equipment - Towbars”,- IATA Airport Handling Manual AHM 958, ”Functional Specification for an Aircraft Towbar”.
A standard type towbar should be equipped with a damping system to protect the nose gear againstjerks and with towing shear pins:- A traction shear pin calibrated at 62000 daN (139381.53 lbf),- A torsion pin calibrated at 4800 m.daN (424778.76 lbf.in).The towing head is designed according to SAE/AS 1614 cat. V.
05-08-00Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
L_AC_050800_1_0010101_01_02
EXAMPLE HOW TO DETERMINE THE MASS REQUIREMENT TO TOW A A380 AT 560 t, AT 1.5% SLOPE,2 ENGINES AT IDLE AND FOR WET TARMAC CONDITIONS:
−ON THE RIGHT HAND SIDE OF THE GRAPH, CHOOSE THE RELEVANT AIRCRAFT WEIGHT (560 t),−FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUIRED SLOPE PERCENTAGE (1.5%),−FROM THE POINT OBTAINED DRAW A STRAIGHT HORIZONTAL LINE UNTIL No. OF ENGINES AT IDLE = 4,−FROM THIS POINT DRAW A PARALLEL LINE TO THE REQUESTED NUMBER OF ENGINES (2),−FROM THIS POINT DRAW A STRAIGHT HORIZONTAL LINE TO THE DRAWBAR PULL AXIS,−THE Y−COORDINATE OBTAINED IS THE NECESSARY DRAWBAR PULL FOR THE TRACTOR (34.4 t),−SEARCH THE INTERSECTION WITH THE "WET CONCRETE" LINE.
THE OBTAINED X−COORDINATE IS THE RECOMMENDED MINIMUM TRACTOR WEIGHT (60.4 t).
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
05-09-00 De-Icing and External Cleaning
**ON A/C A380-800
De-Icing and External Cleaning
1. De-Icing and External Cleaning on GroundThe mobile equipment for aircraft de-icing and external cleaning must be capable of reaching heightsup to approximately 24 m (79 ft).
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
OPERATING CONDITIONS
06-01-00 Engine Exhaust Velocities and Temperatures
**ON A/C A380-800
Engine Exhaust Velocities and Temperatures
1. GeneralThis section shows the estimated engine exhaust efflux velocity and temperature contours forMaximum Take-off, Breakaway and Idle conditions for the A380 engine models.
Contours are available for both Rolls-Royce’s Trent 900 engine and the Engine Alliance’s GP7200engine.
The Maximum Take-off data are presented at the maximum thrust rating for all the A380 enginemodels, including the A380-800F Freighter version. Therefore, contours hereafter include contours ofthe A380-800 Passenger version.
The Breakaway data are presented at a rating corresponding to the minimum thrust level required toinitiate movement of an A380-800F model at its maximum ramp weight from static position and onuphill ground.
The Idle data are directly provided by the engine manufacturers.
In the charts, longitudinal distances are measured from the inboard engine core nozzle exit station,while lateral distances are measured from the aircraft fuselage centreline.
A. Data from Rolls-Royce’s Trent 900:
The estimated efflux data are presented at ISA+15˚C (30˚C), Sea Level Static and negligiblewind conditions.The analysis assumes that the core and bypass streams are fully mixed and calculates the jetbehaviour in free, still air and therefore does not take into account effects such as on-winginstallation, ground entrainment and ambient wind conditions.Velocity contours are presented at 50 ft/s (15 m/s), 100 ft/s (30 m/s) and 150 ft/s (46 m/s),while temperature contours are presented at 104 ˚F (40˚C), 122˚F (50˚C) and 172˚F(60˚C).
B. Data from Engine Alliance’s GP7200:
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
The estimated efflux data are presented at ISA+15˚C (30˚C), Sea Level Static with 20 ktheadwind. It also assumed ground plane and proximity effects. Velocity contours are presentedat 35 MPH (15 m/s), 65 MPH (30 m/s) and 105 MPH (46 m/s), while temperature contoursare presented at 122˚F (50˚C), 212˚F (100˚C) and 392˚F (200˚C). Engine Alliance stronglyrecommends that jet blast studies using their contours include the effect of a 20-knot headwind.
06-01-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-01-01 Engine Exhaust Velocities - Ground Idle Power
**ON A/C A380-800
Engine Exhaust Velocities - Ground Idle Power
1. This section gives engine exhaust velocities at ground idle power.
06-01-01Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
deh0
0023
17
10
20
0
0 40 60
20
80
30
100 120
40 50
140 160
60
180 200
METERS
FEET
ELEVATION
PLAN
0
5
10
15
20
40
60m ft
50 ft/sec(15 m/sec)
100 ft/sec(30 m/sec)
150 ft/sec(46 m/sec)
100 ft/sec(30 m/sec)
150 ft/sec(46 m/sec)
50 ft/sec(15 m/sec)
0
5
10
15
20
40
60
m ft
60
60
60
15
15
15
15
220
L_AC_060101_1_0010101_01_00
Engine Exhaust VelocitiesGround Idle Power - TRENT 900 Engines
FIGURE-06-01-01-991-001-A01
06-01-01Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
ALL VELOCITY VALUES ARE IN STATUE MILES PER HOUR.
FEET(METERS)
GROUND PLANE
CONVERSION FACTOR1 MPH = 1.6 km/h
300
(91)
140(43)
ELEVATION
FEET
(METERS)
0
0
PLAN
150
(46)
0
70(21)
PW
VE
−00
224
(020
7)
AIRPLANECL
105 MPH
65 MPH
35 MPH
DANGER (KEEP OUT) ZONES 35 MPH
(169 km/h)
(105 km/h)
(56 km/h)
105 MPH65 MPH
35 MPH
(169 km/h)(105 km/h)
(56 km/h)
FEET(METERS)
140
0
70(21)
L_AC_060101_1_0020101_01_01
NOTE:
Engine Exhaust VelocitiesGround Idle Power - GP 7200 Engines
FIGURE-06-01-01-991-002-A01
06-01-01Page 3
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-01-02 Engine Exhaust Temperatures - Ground Idle Power
**ON A/C A380-800
Engine Exhaust Temperatures - Ground Idle Power
1. This section gives engine exhaust temperatures at ground idle power.
06-01-02Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
10
20 40 60
20 30
80 100 120
40
140 160
500
0
METERS
FEET
20
40
60
15
0
10
5
m ft
ELEVATION
PLAN
deh0
0023
16
20
40
60
15
0
10
5
m ft
140°F(60°C)
122°F(50°C)
104°F(40°C)
140°F(60°C)
122°F(50°C)
104°F(40°C)
80
100
120
20
25
30
35
L_AC_060102_1_0010101_01_01
GROUND IDLE POWER
Engine Exhaust TemperaturesGround Idle Power - TRENT 900 Engines
FIGURE-06-01-02-991-001-A01
06-01-02Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
FEET(METERS)
GROUND PLANEELEVATIONFEET
(METERS)
0
0
PLAN AIRPLANECL
0
70(21)
0
70(21)
105(32)
ALL TEMPERATURES ARE IN FAHRENHEIT (CELSIUS).
392°F (200°C)
212°F (100°C)
122°F (50°C)
150
(46)
75
(23)
225
(69)
105(32)
35(11)
35(11)
PW
VE
−00
226
(020
7)
392°F (200°C)
122°F (50°C)
212°F (100°C)
NOTE:
L_AC_060102_1_0020101_01_01
Engine Exhaust TemperaturesGround Idle Power - GP 7200 Engines
FIGURE-06-01-02-991-002-A01
06-01-02Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-01-03 Engine Exhaust Velocities - Breakaway Power
**ON A/C A380-800
Engine Exhaust Velocities - Breakaway Power
1. This section gives engine exhaust velocities at breakaway power.
06-01-03Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
deh0
0023
19
100METERS 0
0FEET 40 80
20 40 60 80
120 160 200 240 280 320 360
5
10
1540
60ftm
20
50 ft/sec(15 m/sec)
100 ft/sec(30 m/sec)
150 ft/sec(46 m/sec)
ELEVATION
PLAN
50 ft/sec(15 m/sec)
100 ft/sec(30 m/sec)
150 ft/sec(46 m/sec)
5
10
1540
0
60
ftm
20
0
80
100
120
20
25
30
35
L_AC_060103_1_0010101_01_00
Engine Exhaust VelocitiesBreakaway Power - TRENT 900 Engines
FIGURE-06-01-03-991-001-A01
06-01-03Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
ALL VELOCITY VALUES ARE IN STATUE MILES PER HOUR.
CONVERSION FACTOR1 MPH = 1.6 km/h
PW
VE
−02
200
(020
7)
DANGER (KEEP OUT) ZONES 35 MPH
NOTE:
L_AC_060103_1_0020101_01_01
FEET(METERS)
GROUND PLANE
140(43)
ELEVATION0
70(21)
PLAN AIRPLANECL
FEET
(METERS)
0
0
150
(46)
300
(91)
450
(137)
105 MPH65 MPH
35 MPH(169 km/h)(105 km/h)
(56 km/h)
105 MPH(169 km/h) 65 MPH
(105 km/h) 35 MPH(56 km/h)
FEET
140(43)
0
70(21)
Engine Exhaust VelocitiesBreakaway Power - GP 7200 Engines
FIGURE-06-01-03-991-002-A01
06-01-03Page 3
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-01-04 Engine Exhaust Temperatures - Breakaway Power
**ON A/C A380-800
Engine Exhaust Temperatures - Breakaway Power
1. This section gives engine exhaust temperatures at breakaway power.
06-01-04Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
ELEVATION
20 40 60 80 100 120 140 160
40302010METERS 0
0FEET
520
10
40
60
15
m ft
0
deh0
0023
18
520
10
40
60
15
m ft
PLAN
140°F(60°C)
122°F(50°C)
104°F(40°C)
140°F(60°C)
122°F(50°C)
104°F(40°C)
0
80
100
120
20
25
30
35
180
50
L_AC_060104_1_0010101_01_01
BREAKAWAY POWER(11% MAX TAKE−OFF THRUST)
Engine Exhaust TemperaturesBreakaway Power - TRENT 900 Engines
FIGURE-06-01-04-991-001-A01
06-01-04Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
AIRPLANECL
NOTE : ALL TEMPERATURES ARE IN FAHRENHEIT (CELSIUS).
392°F (200°C)
212°F (100°C)
122°F (50°C)
392°F (200°C)
212°F (100°C)
122°F (50°C)
FEET(METERS)
GROUND PLANEELEVATIONFEET
(METERS)
0
0
PLAN
0
70(21)
0
70(21)
105(32)
150
(46)
75
(23)
225
(69)
105(32)
35(11)
35(11)
PW VE−02201 (0805)
L_AC_060104_1_0020101_01_00
Engine Exhaust TemperaturesBreakaway Power - GP 7200 Engines
FIGURE-06-01-04-991-002-A01
06-01-04Page 3
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-01-05 Engine Exhaust Velocities - Max Take-off Power
**ON A/C A380-800
Engine Exhaust Velocities - Max Take-off Power
1. This section gives engine exhaust velocities at max take-off power.
06-01-05Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
deh0
0023
15
20
100 200 300 400 500 600 700 800
40 60 80 100 120 140 160 180 200 220 240METERS 0
FEET
0
20
10 40
80m ft
TO1800 ft(540 m)
TO1800 ft(540 m)
PLAN
ELEVATION
50 ft/sec(15 m/sec)
100 ft/sec(30 m/sec)
150 ft/sec(46 m/sec)
0
20
10 40
80
m ft
120
160
30
40
60
50 ft/sec(15 m/sec)
100 ft/sec(30 m/sec)
150 ft/sec(46 m/sec)
L_AC_060105_1_0010101_01_00
Engine Exhaust VelocitiesMax. Take-Off Power - TRENT 900 Engines
FIGURE-06-01-05-991-001-A01
06-01-05Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
L_AC_060105_1_0020101_01_01
ALL VELOCITY VALUES ARE IN STATUE MILES PER HOUR.
CONVERSION FACTOR1 MPH = 1.6 km/h
PW
VE
−00
225
(020
7)
DANGER (KEEP OUT) ZONES 35 MPH
NOTE:
FEET(METERS)
GROUND PLANE
300 450 600
140(43)
ELEVATIONFEET
0 150
0
70(21)
(91) (137) (183)0 (46)
(METERS)
PLAN AIRPLANECL
65 MPHOUT TO1090 ft(332 m)
105 MPHOUT TO724 ft(221 m)
35 MPHOUT TO1553 ft(473 m)
FEET(METERS)
140(43)
0
70(21)
65 MPHOUT TO1090 ft(332 m)
105 MPHOUT TO724 ft(221 m)
35 MPHOUT TO1553 ft(473 m)
Engine Exhaust VelocitiesMax. Take-Off Power - GP 7200 Engines
FIGURE-06-01-05-991-002-A01
06-01-05Page 3
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-01-06 Engine Exhaust Temperatures - Max Take-off Power
**ON A/C A380-800
Engine Exhaust Temperatures - Max Take-off Power
1. This section gives engine exhaust temperatures at max take-off power.
06-01-06Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
deh0
0023
14
20METERS 0
FEET 0 40 80 120
40 60
160
80
200 240 280 320
100
360
120
400
20
40
60
10
5
15
0
ftm
ELEVATION
PLAN
20
40
60
10
5
15
0
ftm
80
100
120
15
20
25
30
35
140°F(60 C)
122°F(50 C)
104°F(40 C) TO
540 ft(162 m)
140°F(60 C)
122°F(50 C)
104°F(40 C)
TO540 ft
(162 m)
L_AC_060106_1_0010101_01_01
MAX TAKE−OFF POWER
Engine Exhaust TemperaturesMax Take-Off Power - TRENT 900 Engines
FIGURE-06-01-06-991-001-A01
06-01-06Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
70(21)
35(11)
105(32)
E−00227 (0704)PW V
FEET(METERS)
0ELEVATION
0 PLAN
0
0
FEET
(METERS)
75
(23)
150
(46)
225
(69)
AIRPLANE
GROUND PLANE
392°F (200°C)
212°F (100°C)
122°F (50°C)
392°F (200°C)212°F (100°C)
122°F (50°C)
NOTE : ALL TEMPERATURES ARE IN FAHRENHEIT (CELSIUS).
CL
70(21)
35(11)
105(32)
L_AC_060106_1_0020101_01_00
Engine Exhaust TemperaturesMax Take-Off Power - GP 7200 Engines
FIGURE-06-01-06-991-002-A01
06-01-06Page 3
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-02-00 Airport and Community Noise Data
**ON A/C A380-800
Airport and Community Noise Data
1. Airport and Community Noise Data
06-02-00Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-02-01 Airport and Community Noise Data
**ON A/C A380-800
Airport and Community Noise Data
1. RR TRENT 900 Engines
A. Description of Test ConditionsThe arc of circle (radius = 60m), with microphones 1.2 m high, is centered on the position ofthe noise reference point.A.P.U. : off ; E.C.S. : Packs off.
B. Meteorological DataThe meteorological parameters measured 1.6 m from the ground on the day of test were asfollows:- Temperature: 32˚C- Relative humidity: 31%- Atmospheric pressure: 996 hPa- Wind speed: Negligible- No rain
2. EA GP7200 Engines
A. Description of Test ConditionsThe arc of circle (radius = 60m), with microphones 1.2 m high, is centered on the position ofthe noise reference point.A.P.U. : off ; E.C.S. : Packs off.
B. Meteorological DataThe meteorological parameters measured 1.6 m from the ground on the day of test were asfollows:- Temperature: 12˚C- Relative humidity: 90%- Atmospheric pressure: 1015 hPa- Wind speed: Negligible- No rain
06-02-01Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
0°10°20°
30°
40°
50°
60°
70°
80°
90°
100°
110°
120°
130°
140°
150°160°
170° 180° 190°200°
210°
220°
230°
240°
250°
260°
270°
280°
290°
300°
310°
320°
330°340°350°
DB (A)
75
80
85
90
95
100
105
110
MAX THRUST POSSIBLEON BRAKES
4 ENGINES RUNNING
GROUND IDLE4 ENGINES RUNNING
L_AC_060201_1_0030101_01_01
Airport and Community Noise DataTRENT 900 Engines
FIGURE-06-02-01-991-003-A01
06-02-01Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
0°10°20°
30°
40°
50°
60°
70°
80°
90°
100°
110°
120°
130°
140°
150°160°
170° 180° 190°200°
210°
220°
230°
240°
250°
260°
270°
280°
290°
300°
310°
320°
330°340°350°
DB (A)
75
80
85
90
95
100
105
110
MAX THRUST POSSIBLEON BRAKES
4 ENGINES RUNNING
GROUND IDLE4 ENGINES RUNNING
L_AC_060201_1_0010101_01_01
Airport and Community Noise DataGP 7200 Engines
FIGURE-06-02-01-991-001-A01
06-02-01Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-03-00 Danger Areas of the Engines
**ON A/C A380-800
Danger Areas of the Engines
1. Danger Areas of the Engines
The intake suction danger areas, which are plotted in this chapter, correspond to very low suctionvelocities in order to prevent very low density objects (hat, handkerchief) from ingestion by engines.The primary aim of those danger areas is to protect the people working around the engines.
The A380 outer engines are high enough above ground to prevent the ingestion of typical looseobjects, which can be found on ground at the edge of runways/taxiways paved areas (loose gravelsfor example), in the following conditions:- at usual taxiway thrust (i.e. up to the breakaway power setting), even if the loose objects are
below the A380 outer engines.- at usual take-off thrust (i.e. up to the maximum take-off power setting), if the loose objects are
beyond 3 meters from the A380 outer engines centreline.
06-03-00Page 1
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-03-01 Danger Areas of the Engines - Ground Idle Power
**ON A/C A380-800
Danger Areas of the Engines - Ground Idle Power
1. This section gives danger areas of the engines at ground idle power conditions.
06-03-01Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
deh0
0015
13
INTAKE SUCTION DANGER AREA MINIMUM IDLE POWER
EXHAUST DANGER AREA
ENTRY CORRIDOR
4.5 m(15 ft)
1.3 m(4 ft 3 in)
30TO 70 m (230 ft) AFT OF EXHAUST NOZZLES
L_AC_060301_1_0010101_01_00
Danger Areas of the EnginesGround Idle Power - TRENT 900 Engines
FIGURE-06-03-01-991-001-A01
06-03-01Page 2
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
A
B
15 ft(4.6 m)
5 ft(1.5 m)
A
A
A
B
AREA A − INTAKE SUCTION DANGER AREA
AREA B − ENTRY CORRIDOR
AREA C − EXHAUST DANGER AREA (AFT OF EXHAUST NOZZLE)277 ft (84 m) − GROUND IDLE (20 kt HEADWIND)
33°
PW
VE
−021
97 (0
207)
C
C C
C
L_AC_060301_1_0020101_01_01
Danger Areas of the EnginesGround Idle Power - GP 7200 Engines
FIGURE-06-03-01-991-002-A01
06-03-01Page 3
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@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-03-02 Danger Areas of the Engines - Max. Take-Off Power
**ON A/C A380-800
Danger Areas of the Engines - Max. Take-Off Power
1. This section gives danger areas of the engines at max take-off power conditions.
06-03-02Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
deh0
0015
15
INTAKE SUCTION DANGER AREA MAX TAKE−OFF POWER
EXHAUST DANGER AREA
8.9 m(29 ft)
30TO 548.6 m (1800 ft) AFT OF EXHAUST NOZZLES
L_AC_060302_1_0010101_01_00
Danger Areas of the EnginesMax Take-Off Power - TRENT 900 Engines
FIGURE-06-03-02-991-001-A01
06-03-02Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
AREA B − ENTRY CORRIDOR
AREA C − EXHAUST DANGER AREA (AFT OF EXHAUST NOZZLE)1553 ft (473 m) − MAXIMUM TAKEOFF (20 kt HEADWIND)
B
AREA A − INTAKE SUCTION DANGER AREA
A
C
A
B
C
41°
32 ft(9.8 m)
11 ft(3.4 m)
E−
0219
9 (0
207)
PW
V
L_AC_060302_1_0020101_01_01
Danger Areas of the EnginesMax Take-Off Power - GP 7200 Engines
FIGURE-06-03-02-991-002-A01
06-03-02Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-03-03 Danger Areas of the Engines - Breakaway Power
**ON A/C A380-800
Danger Areas of the Engines - Breakaway Power
1. This section gives danger areas of the engines at breakaway power.
06-03-03Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
deh0
0015
14
INTAKE SUCTION DANGER AREA BREAKAWAY POWER
EXHAUST DANGER AREA
6.0 m(20 ft)4 ENGINE BREAKAWAY
30TO 123.4 m (405 ft) AFT OF EXHAUST NOZZLES
L_AC_060303_1_0010101_01_00
Danger Areas of the EnginesBreakaway Power - TRENT 900 Engines
FIGURE-06-03-03-991-001-A01
06-03-03Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
A
B
C
AREA A − INTAKE SUCTION DANGER AREA
AREA B − ENTRY CORRIDOR
AREA C − EXHAUST DANGER AREA (AFT OF EXHAUST NOZZLE)415 ft (126 m) − BREAKAWAY (20 kt HEADWIND)
B
A A
A
C
38°
PW
VE
−02
198
(020
7)
20 ft(6.10 m)
6.5 ft(1.98 m)
L_AC_060303_1_0020101_01_01
Danger Areas of the EnginesBreakaway Power - GP 7200 Engines
FIGURE-06-03-03-991-002-A01
06-03-03Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-04-00 APU Exhaust Velocities and Temperatures
**ON A/C A380-800
APU Exhaust Velocities and Temperatures
1. APU Exhaust Velocities and Temperatures
06-04-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-04-01 APU Exhaust Velocities and Temperatures
**ON A/C A380-800
APU Exhaust Velocities and Temperatures
1. This section gives APU exhaust velocities and temperatures in max. ECS conditions.
06-04-01Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
DIS
TA
NC
E F
RO
M A
IRC
RA
FT
CE
NT
ER
LIN
E
0 10 20 30 40 50 60 70 80 90 100
30
6
10
20
0
−10
−20
FEET
DIS
TA
NC
E F
RO
M A
IRC
RA
FT
CE
NT
ER
LIN
E
DISTANCE DOWNSTREAM FROM NOZZLEMETERS
10
20
0
−10
−20
FEET
NOTE: THE DATA GIVEN IS BASED ON THE FOLLOWING ASSUMPTIONS:−SEA LEVEL STATIC CONDITIONS−ISA + 23 °C (73 °F)−NO WIND
100
30
DISTANCE DOWNSTREAM FROM NOZZLEMETERS
0 3 6 9 12 15 18 21 24 27
3
0
−3
−6
0 80 90
0 3 6 9 12 15 18 21 24 27
3
6
0
−3
−6
574 °C (1065 °F)
260 °C (500 °F)
149 °C (300 °F)
316 °C (600 °F)
204 °C (400 °F)93 °C (200 °F)
10 20 30 40 50 60 70
46 m/s (150 ft/s)
27 m/s (90 ft/s)
68 m/s (223 ft/s)
37 m/s (120 ft/s)
18 m/s (60 ft/s)
9 m/s (30 ft/s)
L_AC_060401_1_0010101_01_00
APU Exhaust Velocities and TemperaturesMax. ECS Conditions
FIGURE-06-04-01-991-001-A01
06-04-01Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
06-04-02 APU Exhaust Velocities and Temperatures - MES Conditions
**ON A/C A380-800
APU Exhaust Velocities and Temperatures - MES Conditions
1. This section gives the APU exhaust velocities and temperatures in MES conditions.
06-04-02Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
L_AC_060402_0_AAM0_01_00
NOTE: THE DATA GIVEN IS BASED ON THE FOLLOWING ASSUMPTIONS:−SEA LEVEL STATIC CONDITIONS−ISA + 23 °C (73 °F)−NO WIND
0 10 20 30 40 50 60 70 80 90 100
30
10
20
0
−10
−20
FEET
DISTANCE DOWNSTREAM FROM NOZZLEMETERS
10
20
0
−10
−20
FEET100
0 3 6 9 12 15 18 21 24 27 30−6
DIS
TA
NC
E F
RO
M A
IRC
RA
FT
CE
NT
ER
LIN
E
DISTANCE DOWNSTREAM FROM NOZZLEMETERS
0 3 6 9 12 15 18 21 24 27
3
6
0
−3
−6
DIS
TA
NC
E F
RO
M A
IRC
RA
FT
CE
NT
ER
LIN
E
0 10 20 30 40 50 60 70 80 90
3
6
0
−3
458 °C (857 °F)
260 °C (500 °F)
149 °C (300 °F)
316 °C (600 °F)
204 °C (400 °F)
46 m/s (150 ft/s)
27 m/s (90 ft/s)
80 m/s (263 ft/s)
37 m/s (120 ft/s)
18 m/s (60 ft/s)
9 m/s (30 ft/s)
93 °C (200 °F)
L_AC_060402_1_0010101_01_00
APU Exhaust Velocities and TemperaturesMES Conditions
FIGURE-06-04-02-991-001-A01
06-04-02Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
PAVEMENT DATA
07-01-00 General Information
**ON A/C A380-800
General Information
1. GeneralA brief description of the pavement charts that follow will help in airport planning.
To aid in the interpolation between the discrete values shown, each aircraft configuration is shownwith a minimum range of five loads on the Main Landing Gear (MLG).
All curves on the charts represent data at a constant specified tire pressure with:- The aircraft loaded to the Maximum Ramp Weight (MRW),- The CG at its maximum permissible aft position.
Pavement requirements for commercial aircraft are derived from the static analysis of loads imposedon the MLG struts.
Landing Gear Footprint:Section 07-02-00 presents basic data on the landing gear footprint configuration, MRW and tire sizesand pressures.
Maximum Pavement Loads:Section 07-03-00 shows maximum vertical and horizontal pavement loads for certain criticalconditions at the tire-ground interfaces.
Landing Gear Loading on Pavement:Section 07-04-00 contains charts to find these loads throughout the stability limits of the aircraft atrest on the pavement.These MLG loads are used as the point of entry to the pavement design charts which follow,interpolating load values where necessary.
Flexible Pavement Requirements - US Army Corps of Engineers Design Method:Section 07-05-00 uses procedures in Instruction Report No. S-77-1 ”Procedures for Development ofCBR Design Curves”, dated June 1977 and as modified according to the methods described in ICAOAerodrome Design Manual, Part 3. Pavements, 2nd Edition, 1983, Section 1.1 (The ACN-PCNMethod), and utilizing the alpha factors approved by ICAO in October 2007.The report was prepared by the ”U.S. Army Corps Engineers Waterways Experiment Station, Soilsand Pavement Laboratory, Vicksburg, Mississippi”.The line showing 10 000 coverages is used to calculate the Aircraft Classification Number (ACN).
07-01-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
Flexible Pavement Requirements - LCN Conversion Method:The flexible pavement charts in Section 07-06-00 show Load Classification Number (LCN) againstEquivalent Single Wheel Load (ESWL), and ESWL against pavement thickness.All the LCN curves shown in the ’Flexible Pavement Requirements’ were developed from a computerprogram based on data in International Civil Aviation Organization (ICAO) document 7920-AN/865/2, Aerodrome Manual, Part 2, ”Aerodrome Physical Characteristics”, Second Edition, 1965.
Rigid Pavement Requirements - PCA (Portland Cement Association) Design Method:Section 07-07-00 gives the rigid pavement design curves that have been prepared with the use of theWestergaard Equation.This is in general accordance with the procedures outlined in the Portland Cement Associationpublications, ”Design of Concrete Airport Pavement”, 1973 and ”Computer Program for AirportPavement Design” (Program PDILB), 1967 both by Robert G. Packard.
Rigid Pavement Requirements - LCN Conversion:Section 07-08-00 gives data about the rigid pavement requirements for the LCN conversion:- For the radius of relative stiffness,- For the radius of relative stiffness (other values of E and µ).All the LCN curves shown in Rigid Pavement Requirements - LCN conversion were developed from acomputer program based on data in International Civil Aviation Organization (ICAO) document 7920-AN/865/2, Aerodrome Manual, Part 2, ”Aerodrome Physical Characteristics”, Second Edition, 1965.
Rigid Pavement Requirements - LCN Conversion - Radius of Relative Stiffness:The rigid pavement charts show LCN against ESWL, and ESWL against radius of relative stiffness.
Rigid Pavement Requirements - LCN Conversion - Radius of Relative Stiffness (other values of E andµ):The rigid pavement charts show LCN against ESWL, and ESWL against radius of relative stiffnessaffected by the other values of E and µ.
ACN/PCN Reporting System:Section 07-09-00 provides ACN data prepared according to the ACN/PCN system as referenced inICAO Annex 14, ”Aerodromes”, Volume 1 ”Aerodrome Design and Operations” Fourth Edition, July2004, incorporating Amendments 1 to 6.The ACN/PCN system provides a standardized international aircraft/pavement rating systemreplacing the various S, T, TT, LCN, AUW, ISWL, etc., rating systems used throughout the world.ACN is the Aircraft Classification Number and PCN is the corresponding Pavement ClassificationNumber.An aircraft having an ACN less than or equal to the PCN can operate without restriction on thepavement.Numerically the ACN is two times the derived single wheel load expressed in thousands of kilograms.The derived single wheel load is defined as the load on a single tire inflated to 1.25 MPa (181 psi)that would have the same pavement requirements as the aircraft.
07-01-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
Computationally the ACN/PCN system uses PCA program PDILB for rigid pavements and S-77-1 forflexible pavements to calculate ACN values.
The Airport Authority must decide on the method of pavement analysis and the results of theirevaluation shown as follows:
PCNPAVEMENT TYPE SUBGRADE
CATEGORYTIRE PRESSURE
CATEGORYEVALUATION
METHODR - Rigid A - High W - No pressure limit T - Technical
F - Flexible B - Medium X - High pressure limitedto 1.75 MPa (254 psi)
U - Using Aircraft
C - Low Y - Medium pressurelimited to 1.25 MPa (181psi)
D - Ultra Low Z - Low pressure limitedto 0.5 MPa (73 psi)
For flexible pavements, the four subgrade categories are:
- A. High Strength CBR 15
- B. Medium Strength CBR 10
- C. Low Strength CBR 6
- D. Ultra Low Strength CBR 3
For rigid pavements, the four subgrade categories are:
- A. High Strength Subgrade k = 150 MN/m3 (550 pci)
- B. Medium Strength Subgrade k = 80 MN/m3 (300 pci)
- C. Low Strength Subgrade k = 40 MN/m3 (150 pci)
- D. Ultra Low Strength Subgradek
= 20 MN/m3 (75 pci)
07-01-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
07-02-00 Landing Gear Footprint
**ON A/C A380-800
Landing Gear Footprint
1. This section gives data about the landing gear footprint in relation with the aircraft Maximum RampWeight (MRW) and tire sizes and pressures.The landing gear footprint information is given for all the aircraft operational weight variants.
07-02-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
1.05
0 m
(3.4
45 ft
)
1.53
0 m
(5.0
20 ft
)
NO
SE
LA
ND
ING
GE
AR
12.4
56 m
(40.
866
ft)
WIN
G L
AN
DIN
GG
EA
R
BO
DY
LA
ND
ING
GE
AR
(5.0
85 ft
)1.
550
m
5.26
4 m
(17.
270
ft)
(5.0
20 ft
)1.
530
m
(5.5
77 ft
)1.
700
m(5
.577
ft)
1.70
0 m
1.35
0 m
(4.4
29 ft
)
(5.5
77 ft
)1.
700
m
(93.
848
ft)28
.605
m
(104
.596
ft)
31.8
81 m
L_AC_070200_1_0030101_01_01
Landing Gear Footprint(Sheet 1 of 2) (Sheet 1 of 2)
FIGURE-07-02-00-991-003-A01
07-02-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
WE
IGH
TV
AR
IAN
TM
AX
IMU
MR
AM
PW
EIG
HT
WV
005
WV
006
WV
007
WV
008
WV
009
WV
004
WV
000
WV
001
WV
002
WV
003
562
000
kg(1
239
000
lb)
512
000
kg(1
128
775
lb)
571
000
kg(1
258
850
lb)
512
000
kg(1
128
775
lb)
562
000
kg(1
239
000
lb)
575
000
kg(1
267
650
lb)
492
000
kg(1
084
675
lb)
577
000
kg(1
272
075
lb)
537
000
kg(1
183
875
lb)
562
000
kg(1
239
000
lb)P
ER
CE
NT
AG
EO
F W
EIG
HT
ON
MA
ING
EA
R G
RO
UP
NO
SE
GE
AR
TIR
EP
RE
SS
UR
EN
OS
E G
EA
RT
IRE
SIZ
E
95.1
%
94.3
%
95.1
%
94.3
%
95.1
%
95.1
%
95.1
%14
.1 b
ar(2
05 p
si)
95.1
%
94.3
%
95.1
%
1 27
0x45
5 R
22 3
2PR
OR
50x
20 R
22 3
4PR
WIN
G G
EA
RT
IRE
SIZ
E
15 b
ar(2
18 p
si)
1 40
0x53
0 R
23 4
0PR
BO
DY
GE
AR
TIR
E S
IZE
WIN
GG
EA
R T
IRE
PR
ES
SU
RE
BO
DY
GE
AR
TIR
EP
RE
SS
UR
E
14.1
bar
(205
psi
)
14.1
bar
(205
psi
)
14.1
bar
(205
psi
)
14.1
bar
(205
psi
)
14.1
bar
(205
psi
)
14.1
bar
(205
psi
)
14.1
bar
(205
psi
)
14.1
bar
(205
psi
)
14.1
bar
(205
psi
)
14 b
ar(2
03 p
si)
14 b
ar(2
03 p
si)
14 b
ar(2
03 p
si)
15 b
ar(2
18 p
si)
15 b
ar(2
18 p
si)
15 b
ar(2
18 p
si)
15 b
ar(2
18 p
si)
15 b
ar(2
18 p
si)
15 b
ar(2
18 p
si)
1 27
0x45
5 R
22 3
2PR
OR
50x
20 R
22 3
4PR
1 27
0x45
5 R
22 3
2PR
OR
50x
20 R
22 3
4PR
1 27
0x45
5 R
22 3
2PR
OR
50x
20 R
22 3
4PR
1 27
0x45
5 R
22 3
2PR
OR
50x
20 R
22 3
4PR
1 27
0x45
5 R
22 3
2PR
OR
50x
20 R
22 3
4PR
1270
x455
R22
32P
RO
R 5
0x20
R22
34P
R
1 27
0x45
5 R
22 3
2PR
OR
50x
20 R
22 3
4PR
1 27
0x45
5 R
22 3
2PR
OR
50x
20 R
22 3
4PR
1 27
0x45
5 R
22 3
2PR
OR
50x
20 R
22 3
4PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
15 b
ar(2
18 p
si)
14 b
ar(2
03 p
si)
14 b
ar(2
03 p
si)
14 b
ar(2
03 p
si)
15 b
ar(2
18 p
si)
15 b
ar(2
18 p
si)
15 b
ar(2
18 p
si)
15 b
ar(2
18 p
si)
15 b
ar(2
18 p
si)
15 b
ar(2
18 p
si)
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
1 40
0x53
0 R
23 4
0PR
L_AC_070200_1_0030102_01_00
Landing Gear Footprint(Sheet 2 of 2) (Sheet 2 of 2)
FIGURE-07-02-00-991-003-A01
07-02-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
07-03-00 Maximum Pavement Loads
**ON A/C A380-800
Maximum Pavement Loads
1. This section shows maximum vertical and horizontal pavement loads for some critical conditions atthe tire-ground interfaces.The maximum pavement loads are given for all the aircraft operational weight variants.
07-03-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
H
V(W
G)
MA
XIM
UM
VE
RT
ICA
L N
OS
E G
EA
R G
RO
UN
D L
OA
D A
T M
OS
T F
WD
CG
V(N
G)
MA
XIM
UM
VE
RT
ICA
L W
ING
GE
AR
GR
OU
ND
LO
AD
AT
MA
X A
FT
CG
HM
AX
IMU
M V
ER
TIC
AL
BO
DY
GE
AR
GR
OU
ND
LO
AD
AT
MA
X A
FT
CG
MA
XIM
UM
HO
RIZ
ON
TA
L G
RO
UN
D L
OA
D F
RO
M B
RA
KIN
GV
(BG
)
V(B
G)
12
34
56
(PE
R S
TR
UT
)
V(W
G)
H (
PE
R S
TR
UT
)
WV
000
WE
IGH
TV
AR
IAN
T
MA
XIM
UM
RA
MP
WE
IGH
TA
TS
TA
TIC
LO
AD
MO
ST
FW
D C
GA
T 1
0 ft/
s²D
EC
ELE
RA
TIO
N
AT
ST
AT
IC L
OA
D
MA
X A
FT
CG
BR
AK
ING
CO
EF
FIC
IEN
T =
0.8
562
000
kg(1
239
000
lb)
BR
AK
ING
INS
TA
NT
AN
EO
US
106
920
kg(2
35 7
25 lb
)16
0 38
0 kg
(353
575
lb)
97 4
10 k
g(2
14 7
50 lb
)14
6 11
0 kg
(322
125
lb)
107
720
kg(2
37 4
75 lb
)16
1 57
0 kg
(356
200
lb)
97 4
10 k
g(2
14 7
50 lb
)14
6 11
0 kg
(322
125
lb)
37.5
%M
AC
(a)
43 %
MA
C(a
)
35.8
1 %
MA
C(a
)
37.8
%M
AC
(a)
35.8
1 %
MA
C(a
)
43 %
MA
C(a
)
41 %
MA
C(a
)
43 %
MA
C(a
)
V(N
G)
WV
001
WV
002
WV
003
512
000
kg(1
128
775
lb)
571
000
kg(1
258
850
lb)
512
000
kg(1
128
775
lb)
39 8
30 k
g(8
7 80
0 lb
)
39 7
60 k
g(8
7 67
5 lb
)
39 7
80 k
g(8
7 70
0 lb
)
39 7
60 k
g(8
7 67
5 lb
)
69 4
30 k
g(1
53 0
75 lb
)
66 7
30 k
g(1
47 1
25 lb
)
69 8
50 k
g(1
54 0
00 lb
)
66 7
30 k
g(1
47 1
25 lb
)
43 %
MA
C(a
)
(PE
R S
TR
UT
)
V(B
G)
43 %
MA
C(a
)
41 %
MA
C(a
)
43 %
MA
C(a
)
ST
AT
IC
AT
ST
AT
IC L
OA
D
MA
X A
FT
CG
AT
10
ft/s²
DE
CE
LER
AT
ION
BR
AK
ING
ST
EA
DY
7
34 9
30 k
g(7
7 02
5 lb
)52
400
kg
(115
525
lb)
85 5
40 k
g(1
88 5
75 lb
)12
8 31
0 kg
(282
875
lb)
31 8
30 k
g(7
0 17
5 lb
)47
740
kg
(105
250
lb)
77 9
30 k
g(1
71 8
00 lb
)11
6 89
0 kg
(257
700
lb)
35 4
90 k
g(7
8 25
0 lb
)53
240
kg
(117
375
lb)
86 1
70 k
g(1
89 9
75 lb
)12
9 26
0 kg
(284
975
lb)
31 8
30 k
g(7
0 17
5 lb
)47
740
kg
(105
250
lb)
77 9
30 k
g(1
71 8
00 lb
)11
6 89
0 kg
(257
700
lb)
(c)
(b)
(c)
(b)
(c)
(b)
(c)
(b)
(c)
(b)
(c)
(b)
(c)
(b)
(c)
(b)
AT
NO
TE
:
V(W
G)
V(N
G)
(a)
LOA
DS
CA
LCU
LAT
ED
US
ING
AIR
CR
AF
T A
T M
RW
(b)
BR
AK
ED
WIN
G G
EA
R(c
) B
RA
KE
D B
OD
Y G
EA
R
L_AC_070300_1_0060101_01_00
Maximum Pavement Loads(Sheet 1 of 2) (Sheet 1 of 2)
FIGURE-07-03-00-991-006-A01
07-03-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
NO
TE
:(a
) LO
AD
S C
ALC
ULA
TE
D U
SIN
G A
IRC
RA
FT
AT
MR
W(b
) B
RA
KE
D W
ING
GE
AR
(c)
BR
AK
ED
BO
DY
GE
AR
12
34
56
(PE
R S
TR
UT
)
V(W
G)
H (
PE
R S
TR
UT
)
WV
004
WE
IGH
TV
AR
IAN
T
MA
XIM
UM
RA
MP
WE
IGH
TA
TS
TA
TIC
LO
AD
MO
ST
FW
D C
GA
T 1
0 ft/
s²D
EC
ELE
RA
TIO
N
AT
ST
AT
IC L
OA
D
MA
X A
FT
CG
BR
AK
ING
CO
EF
FIC
IEN
T =
0.8
562
000
kg(1
239
000
lb)
BR
AK
ING
INS
TA
NT
AN
EO
US
106
920
kg(2
35 7
25 lb
)16
0 38
0 kg
(353
575
lb)
108
470
kg(2
39 1
25 lb
)16
2 70
0 kg
(358
700
lb)
93 6
00 k
g(2
06 3
50 lb
)14
0 41
0 kg
(309
550
lb)
37.5
%M
AC
(a)
43 %
MA
C(a
)
37.8
%M
AC
(a)
35.0
6 %
MA
C(a
)
41 %
MA
C(a
)
43 %
MA
C(a
)
V(N
G)
WV
005
WV
006
WV
007
575
000
kg(1
267
650
lb)
492
000
kg(1
084
675
lb)
39 8
30 k
g(8
7 80
0 lb
)
40 0
50 k
g(8
8 30
0 lb
)
39 7
00 k
g(8
7 52
5 lb
)
69 4
30 k
g(1
53 0
75 lb
)
70 3
40 k
g(1
55 0
75 lb
)
65 6
10 k
g(1
44 6
50 lb
)
43 %
MA
C(a
)
(PE
R S
TR
UT
)
V(B
G)
41 %
MA
C(a
)
43 %
MA
C(a
)
ST
AT
IC
AT
ST
AT
IC L
OA
D
MA
X A
FT
CG
AT
10
ft/s²
DE
CE
LER
AT
ION
BR
AK
ING
ST
EA
DY
7
34 9
30 k
g(7
7 02
5 lb
)52
400
kg
(115
525
lb)
85 5
40 k
g(1
88 5
75 lb
)12
8 31
0 kg
(282
875
lb)
35 7
40 k
g(7
8 80
0 lb
)53
610
kg
(118
200
lb)
86 7
80 k
g(1
91 3
00 lb
)13
0 16
0 kg
(286
950
lb)
30 5
80 k
g(6
7 42
5 lb
)45
880
kg(1
01 1
50 lb
)
74 8
80 k
g(1
65 1
00 lb
)11
2 32
0 kg
(247
625
lb)
(c)
(b)
(c)
(b)
(c)
(b)
(c)
(b)
(c)
(b)
(c)
(b)
AT
108
850
kg(2
39 9
75 lb
)16
3 27
0 kg
(359
950
lb)
102
170
kg(2
25 2
25 lb
)15
3 25
0 kg
(337
850
lb)
37.8
%M
AC
(a)
36.7
2 %
MA
C(a
)
41 %
MA
C(a
)
43 %
MA
C(a
)
WV
008
WV
009
577
000
kg(1
272
075
lb)
537
000
kg(1
183
875
lb)
40 1
90 k
g(8
8 60
0 lb
)
39 7
40 k
g(8
7 60
0 lb
)
70 5
90 k
g(1
55 6
25 lb
)
68 0
30 k
g(1
49 9
75 lb
)
41 %
MA
C(a
)
43 %
MA
C(a
)
35 8
70 k
g(7
9 07
5 lb
)53
800
kg
(118
600
lb)
87 0
80 k
g(1
91 9
75 lb
)13
0 62
0 kg
(287
950
lb)
33 3
80 k
g(7
3 60
0 lb
)50
070
kg
(110
400
lb)
81 7
30 k
g(1
80 2
00 lb
)12
2 60
0 kg
(270
275
lb)
(c)
(b)
(c)
(b)
(c)
(b)
(c)
(b)
562
000
kg(1
239
000
lb)
106
920
kg(2
35 7
25 lb
)16
0 38
0 kg
(353
575
lb)
37.5
%M
AC
(a)
43 %
MA
C(a
)
39 8
30 k
g(8
7 80
0 lb
)69
430
kg
(153
075
lb)
43 %
MA
C(a
)
34 9
30 k
g(7
7 02
5 lb
)52
400
kg
(115
525
lb)
85 5
40 k
g(1
88 5
75 lb
)12
8 31
0 kg
(282
875
lb)
(c)
(b)
(c)
(b)
L_AC_070300_1_0060102_01_00
Maximum Pavement Loads(Sheet 2 of 2) (Sheet 2 of 2)
FIGURE-07-03-00-991-006-A01
07-03-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
07-04-00 Landing Gear Loading on Pavement
**ON A/C A380-800
Landing Gear Loading on Pavement
1. This section gives data about landing gear loading on pavement.The MLG loading on pavement graphs are given for the weight variants that produce (at the MRWand max aft CG) the lowest MLG load and the highest MLG load for each type of aircraft.
2. MLG Loading on PavementExample, see FIGURE 7-4-0-991-001-A (sheet 1), calculation of the total weight on the MLG for:- An aircraft with a MRW of 492 000 kg (1 084 675 lb),- The aircraft gross weight is 420 000 kg (925 950 lb).- A percentage of weight on the MLG of 95.1% (percentage of weight on the MLG at MRW and
max aft CG).The total weight on the MLG group is 399 530 kg (880 800 lb).
3. Wing Gear and Body Gear Loading on PavementThe MLG group consists of two wing gears (4-wheel bogies) plus two body gears (6-wheel bogies).
Example, see FIGURE 7-4-0-991-001-A (sheet 2), calculation of the total weight on the MLG for:- An aircraft with a MRW of 492 000 kg (1 084 675 lb),- The aircraft gross weight is 420 000 kg (925 950 lb).The load on the two wing gears is 159 810 kg (352 325 lb) and the load on the two body gears is239 720 kg (528 475 lb).The total weight on the MLG group is 399 530 kg (880 800 lb).
NOTE : The CG in the figure title is the CG used for ACN/LCN calculation.
07-04-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
Landing Gear Loading on PavementWV008, MRW 577 000 kg CG 41% (Sheet 1 of 2) (Sheet 1 of 2)
FIGURE-07-04-00-991-002-A01
07-04-00Page 4
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
100
120
140
160
180
200
220
240
260
280
300
320
340 26
028
030
032
034
036
038
040
042
044
046
048
050
052
054
056
058
060
0
LOAD ON CENTER GEARS OR LOAD ON WING GEARS (x 1 000 kg)
AIR
CR
AF
T G
RO
SS
WE
IGH
T (
x 1
000
kg)
600
700
800
900
1 00
01
100
1 20
01
300
(x 1
000
lb)
300
400
500
600
700
(x 1 000 lb)
BO
DY
GE
AR
S
WIN
G G
EA
RS
L_AC_070400_1_0020102_01_00
Landing Gear Loading on PavementWV008, MRW 577 000 kg, CG 41% (Sheet 2 of 2) (Sheet 2 of 2)
FIGURE-07-04-00-991-002-A01
07-04-00Page 5
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
07-05-00 Flexible Pavement Requirements - US Army Corps of Engineers Design Method
**ON A/C A380-800
Flexible Pavement Requirements - US Army Corps of Engineers Design Method
1. This section gives data about the flexible pavement requirements.The flexible pavement requirements graphs are given at standard tire pressure for the weight variantsthat produce (at the MRW and max aft CG) the lowest MLG and the highest MLG load of each typeof aircraft.They are calculated with the US Army Corps of Engineers Design Method.To find a flexible pavement thickness, you must know the Subgrade Strength (CBR), the annualdeparture level and the weight on one MLG.The line that shows 10 000 coverages is used to calculate the Aircraft Classification Number (ACN).The procedure that follows is used to develop flexible pavement design curves:- With the scale for pavement thickness at the bottom and the scale for CBR at the top, a random
line is made to show 10 000 coverages,- A plot is then made of the incremental values of the weight on the MLG,- Annual departure lines are made based on the load lines of the weight on the MLG that is shown
on the graph.
Example, see FIGURE 7-5-0-991-001-A (Sheet 1), calculation of the thickness of the flexiblepavement for Wing Landing Gear:- An aircraft with a MRW of 492 000 kg (1 084 675 lb),- A ”CBR” value of 10,- An annual departure level of 3 000,- The load on one WLG of 75 000 kg (165 350 lb).The required flexible pavement thickness is 58.5 cm (23 in).
Example, see FIGURE 7-5-0-991-001-A (Sheet 2), calculation of the thickness of the flexiblepavement for Body Landing Gear:- An aircraft with a Maximum Ramp Weight (MRW) of 492 000 kg (1 084 675 lb),- A ”CBR” value of 10,- An annual departure level of 3 000,- The load on one BLG of 125 000 kg (275 575 lb).The required flexible pavement thickness is 61.1 cm (24 in).
NOTE : The CG in the figure title is the CG used for ACN calculation.
07-05-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
10 000 COVERAGES USED
MAXIMUM POSSIBLE WINGLANDING GEAR LOAD ATMAXIMUM RAMP WEIGHT
SUBGRADE STRENGTH − CBR
8060403020151063
8060403020151063
FLEXIBLE PAVEMENT THICKNESS
1 400 x 530 R23 40PR TIRES
TIRE PRESSURE CONSTANT AT 14 bar (203 psi)
10 15 20 30 40 60 80 100 120 150 180
FOR ACN CALCULATIONSALPHA FACTOR = 0.8
WEIGHT ON ONE WING LANDING GEAR93 600 kg (206 350 lb)
60 000 kg (132 275 lb)45 000 kg (99 200 lb)30 000 kg (66 150 lb)
1. This section gives data about the flexible pavement requirements for Load Classification Number(LCN) conversion.The flexible pavement requirements graphs are given at standard tire pressure for the weight variantsproducing (at the MRW and maximum aft CG) the lowest MLG load and the highest MLG load foreach A/C type.To find the aircraft weight that a flexible pavement can support, you must know the LCN of thepavement and the thickness.
Example, see FIGURE 7-6-0-991-002-A (sheet 1), calculation of the thickness of the flexiblepavement for the WLG:- An aircraft with a MRW of 492 000 kg (1 084 675 lb),- The flexible pavement thickness is 1 270 mm (50 in) with a related LCN of 112.The weight on one MLG is 75 000 kg (165 350 lb).
Example, see FIGURE 7-6-0-991-002-A (sheet 2), calculation of the thickness of the flexiblepavement for the BLG:- An aircraft with a MRW of 492 000 kg (1 084 675 lb),- The flexible pavement thickness is 1 270 mm (50 in) with a related LCN of 104.The weight on one MLG is 125 000 kg (275 575 lb).
2. Flexible Pavement Requirements - LCN TableThe table in FIGURE 7-6-0-991-001-A provides LCN data in a tabular format similar to the one usedby ICAO in the ”Aerodrome Design Manual Part 3, Pavements - Edition 1977”. In order to use thesystem accurately you should know the total pavement thickness for flexible pavement.However, the pavement thickness for particular runways are not frequently published in the standardairport information sources (Jeppesen, AERAD, DOD, etc.).Therefore it is common practice to use a standard thickness (20 in) when determining the LCN andthe ESWL of the aircraft.
If the LCN for an intermediate weight between the MRW and the empty weight of the aircraft isrequired or if the real thickness is known, refer to the figures that follow.
NOTE : The CG in the figure title is the CG used for LCN calculation.
07-06-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
WEIGHTVARIANT
WV000
ALL UPMASS (kg)
LOAD ONONE MAINGEAR LEG
(%)
TIREPRESSURE
(MPa)
FLEXIBLE PAVEMENTESWL
x 1 000 kg
h = 510 mm (20 in)x 1 000 lb
LCN
562 00019 (WLG)28.5 (BLG)
2827
6259
9996
300 00019 (WLG)28.5 (BLG)
512 00019 (WLG)28.5 (BLG)
WV001300 000
19 (WLG)28.5 (BLG)
WV002571 000
18.9 (WLG)28.3 (BLG)
28
300 00018.9 (WLG)28.3 (BLG)
14
WV003512 000
19 (WLG)28.5 (BLG)
25
300 00019 (WLG)28.5 (BLG)
14
WV004562 000
19 (WLG)28.5 (BLG)
28
300 00019 (WLG)28.5 (BLG)
14
WV005562 000
19 (WLG)28.5 (BLG)
28
300 00019 (WLG)28.5 (BLG)
14
WV006575 000
18.9 (WLG)28.3 (BLG)
28
300 00018.9 (WLG)28.3 (BLG)
14
WV007492 000
19 (WLG)28.5 (BLG)
24
300 00019 (WLG)28.5 (BLG)
14
WV008577 000
18.9 (WLG)28.3 (BLG)
28
300 00018.9 (WLG)28.3 (BLG)
14
WV009537 000
19 (WLG)28.5 (BLG)
26
300 00019 (WLG)
28.5 (BLG)14
1.40
1.50
1.50
1.50
1.50
1.40
1.40
1.50
1.50
1.50
141425241414
27
14
24
14
27
14
27
14
27
14
23
14
27
14
26
14 31 56
57 93
31 55
59 98
31 54
31 56
53 85
31 54
59 97
31 55
53 85
31 54
59 96
31 56
59 96
31 56
59 97
31 55
51 83
55
31
62
31
55
31
62
31
62
31
62
31
53
31
62
31
57
31
56
88
54
100
55
88
54
99
56
99
56
101
55
85
54
101
55
96
56
31
L_AC_070600_1_0010101_01_00
Flexible Pavement RequirementsLCN Table
FIGURE-07-06-00-991-001-A01
07-06-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
07-07-00 Rigid Pavement Requirements - Portland Cement Association Design Method
**ON A/C A380-800
Rigid Pavement Requirements - Portland Cement Association Design Method
1. This section gives data about the rigid pavement requirements for the PCA (Portland CementAssociation) design method.The rigid pavement requirement graphs are given at standard tire pressure for the weight variantsproducing (at the MRW and max aft CG) the lowest MLG load and the highest MLG load for eachA/C type.To find a rigid pavement thickness, you must know the Subgrade Modulus (k), the permitted workingstress and the weight on one MLG.The procedure that follows is used to develop rigid pavement design curves:- With the scale for pavement thickness on the left and the scale for permitted working stress on
the right, a random load line is made. This represents the MLG maximum weight to be shown,- A plot is then made of all values of the subgrade modulus (k values),- More load lines for the incremental values of the weight on the MLG are made based on the
curve for k = 80 MN/m3, which is already shown on the graph.
Example, see FIGURE 7-7-0-991-001-A (sheet 1), calculation of the thickness of the rigid pavementfor the WLG:- An aircraft with a MRW of 492 000 kg (1 084 675 lb),- A k value of 80 MN/m3 (300 lbf/in3),- A permitted working stress of 38.67 kg/cm2 (550 lb/in2),- The load on one MLG is 75 000 kg (165 350 lb).The required rigid pavement thickness is 224 mm (9 in).
Example, see FIGURE 7-7-0-991-001-A (sheet 2), calculation of the thickness of the rigid pavementfor the BLG:- An aircraft with a MRW of 492 000 kg (1 084 675 lb),- A k value of 80 MN/m3 (300 lbf/in3),- A permitted working stress of 38.67 kg/cm2 (550 lb/in2),- The load on one MLG is 125 000 kg (275 575 lb).The required rigid pavement thickness is 239 mm (9 in).
NOTE : The CG in the figure title is the CG used for ACN calculation.
07-07-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
1 400 x 530 R23 40PR TIRESTIRE PRESSURE CONSTANT AT 14 bar (203 psi)
60
50
40
30
20
10
100
200
300
400
500
600
700
800
90015
14
38
36
34
32
13
1230
28 11
26
24
22
10
9
20
18 7
8
(kg/
cm²)
ALL
OW
AB
LE W
OR
KIN
G S
TR
ES
S
(lb/in
²)
RIG
ID P
AV
EM
EN
T T
HIC
KN
ES
S(c
m)
(in)
FOR LOADS LESS THAN MAXIMUM,EXACT.LINE AND ANY VALUES FOR k ARETHE MAXIMUM LOAD REFERENCETHE VALUES OBTAINED BY USINGNOTE:
THE CURVES ARE EXACT FOR k =80 MN/m³ BUT DEVIATE SLIGHTLYFOR ANY OTHER VALUES OF k.
PDILB" PORTLAND CEMENTPAVEMENT DESIGN − PROGRAMPROGRAM FOR AIRPORTPAVEMENTS" AND "COMPUTER"DESIGN OF CONCRETE AIRPORTREFERENCE:
ASSOCIATION.
k = 150 MN/m³k = 80 MN/m³k = 40 MN/m³k = 20 MN/m³
45 000 kg60 000 kg (132 275 lb)75 000 kg (165 350 lb)93 600 kg (206 350 lb)LANDING GEARWEIGHT ON ONE WING
1. This section gives data about the rigid pavement requirements for the Load Classification Number(LCN) conversion (radius of relative stiffness).The rigid pavement requirement graphs are given at standard tire pressure for the weight variantsproducing (at the MRW and max aft CG) the lowest MLG load and the highest MLG load for eachtype of aircraft.To find the aircraft weight that a rigid pavement can support, you must know the LCN of thepavement and the radius of relative stiffness (L).The calculation of the radius of relative stiffness (L) is done with the formula and the table given in”Radius of Relative Stiffness” (L values based on Young’s Modulus (E) of 4 000 000 psi andPoisson’s Ratio (µ) of 0.15), see FIGURE 7-8-0-991-002-A.
Example, see FIGURE 7-8-0-991-003-A (Sheet 1), calculation of the aircraft weight through theradius of relative stiffness (L) of the rigid pavement for the Wing Landing Gear (WLG):- An aircraft with a MRW of 492 000 kg (1 084 675 lb),- The radius of relative stiffness is shown at 1 270 mm (50 in) with a related LCN of 86.The weight on one WLG is 75 000 kg (165 350 lb).
Example, see FIGURE 7-8-0-991-003-A (Sheet 2), calculation of the aircraft weight through theradius of relative stiffness (L) of the rigid pavement for the Body Landing Gear (BLG):- An aircraft with a MRW of 492 000 kg (1 084 675 lb),- The radius of relative stiffness is shown at 1 270 mm (50 in) with a related LCN of 81.The weight on one BLG is 125 000 kg (275 575 lb).
The following table provides LCN data in a tabular format similar to the one used by ICAO in the”Aerodrome Design Manual Part 3, Pavements - Edition 1977”. In order to use the system accuratelyyou should know the total pavement radius of relative stiffness (L-value) for rigid pavement.However, the pavement radius of relative stiffness for a particular runway are not frequently publishedin the standard airport information sources (Jeppesen, AERAD, DOD, etc.). Therefore it is commonpractice to use a standard radius of relative stiffness (30 inches) when determining the LCN and theESWL of the aircraft.If the LCN for an intermediate weight between the maximum ramp weight and the empty weight ofthe aircraft is required or if the real thickness is known, refer to the figures that follow.
2. Radius of Relative Stiffness (Other values of E and µ)This section gives data about the rigid pavement requirements for the Load Classification Number(LCN) conversion (radius of relative stiffness) with other values of E (Young’s modulus) and µ(Poisson’s ratio).The other values of E and µ have an effect on the radius of relative stiffness (L-value).
07-08-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
The effect of E and µ on the radius of relative stiffness (L-value) is shown in the graphs in FIGURE7-8-0-991-005-A.The table in FIGURE 7-8-0-991-002-A shows L-values based on a Young’s modulus (E) of 4 000 000psi and a Poisson’s ratio (µ) of 0.15.To find the L-value, you must know the values of E and µ.Example, see FIGURE 7-8-0-991-005-A, calculation of the L-values of the rigid pavement for an E of3 000 000 psi.The ”E” factor is 0.931.The radius of relative stiffness (L-value) is the value found in the table (see FIGURE 7-8-0-991-002-A) multiplied by 0.931.
NOTE : The CG in the figure title is the CG used for LCN calculation.
07-08-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
WEIGHTVARIANT
WV000
ALL UPMASS (kg)
LOAD ONONE MAINGEAR LEG
(%)
TIREPRESSURE
(MPa)
RIGID PAVEMENTESWL
x 1 000 kg
L = 760 mm (30 in)x 1 000 lb
LCN
562 00019 (WLG)28.5 (BLG)
269
5820
9574
300 00019 (WLG)28.5 (BLG)
512 00019 (WLG)28.5 (BLG)
WV001300 000
19 (WLG)28.5 (BLG)
WV002571 000
18.9 (WLG)28.3 (BLG)
27
300 00018.9 (WLG)28.3 (BLG)
14
WV003512 000
19 (WLG)28.5 (BLG)
24
300 00019 (WLG)28.5 (BLG)
14
WV004562 000
19 (WLG)28.5 (BLG)
26
300 00019 (WLG)28.5 (BLG)
14
WV005562 000
19 (WLG)28.5 (BLG)
26
300 00019 (WLG)28.5 (BLG)
14
WV006575 000
18.9 (WLG)28.3 (BLG)
27
300 00018.9 (WLG)28.3 (BLG)
14
WV007492 000
19 (WLG)28.5 (BLG)
23
300 00019 (WLG)28.5 (BLG)
14
WV008577 000
18.9 (WLG)28.3 (BLG)
27
300 00018.9 (WLG)28.3 (BLG)
14
WV009537 000
19 (WLG)28.5 (BLG)
25
300 00019 (WLG)
28.5 (BLG)14
1.40
1.50
1.50
1.50
1.50
1.40
1.40
1.50
1.50
1.50
145
248
145
9
5
8
5
9
5
9
5
9
5
8
5
9
5
8
5 11 41
18 71
11 40
20 75
11 40
11 41
18 66
11 40
20 74
11 40
18 66
11 40
20 74
11 41
20 74
11 41
20 75
11 40
18 64
53
31
59
31
53
31
58
31
58
31
59
31
51
31
59
31
55
31
53
84
51
96
53
84
51
95
53
95
53
96
53
82
51
97
53
92
53
31
L_AC_070800_1_0010101_01_00
Rigid Pavement RequirementsLCN Table
FIGURE-07-08-00-991-001-A01
07-08-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
6.06.57.07.5
31.4833.4335.3437.22
29.3031.1132.8934.63
26.4728.1129.7231.29
24.6326.1627.6529.12
23.3024.7426.1527.54
22.2623.6424.9926.32
21.4222.7424.0425.32
20.7222.0023.2524.49
19.1320.3121.4722.61
8.08.59.09.5
39.0640.8842.6744.43
36.3538.0439.7141.35
32.8534.3735.8837.36
30.5731.9933.3934.77
28.9130.2531.5832.89
27.6228.9130.1731.42
26.5827.8129.0330.23
25.7026.9028.0829.24
23.7424.8425.9327.00
10.010.511.011.5
46.1847.9049.6051.28
38.8340.2841.7143.12
36.1437.4838.8140.13
34.1735.4536.7137.95
32.6533.8735.0736.26
31.4232.5933.7534.89
30.3931.5232.6433.74
28.0629.1130.1431.16
12.012.513.013.5
52.9454.5956.2257.83
49.2750.8052.3253.82
44.5245.9047.2748.63
41.4342.7243.9945.26
39.1840.4041.6142.80
37.4438.6039.7540.89
36.0237.1438.2539.35
34.8435.9236.9938.06
32.1733.1734.1635.14
14.014.515.015.5
16.016.517.017.5
55.3156.7858.2559.70
65.6967.2368.7570.26
61.1362.5663.9865.38
49.9851.3152.6353.94
46.5147.7548.9850.20
43.9845.1646.3247.47
55.2456.5357.8159.08
51.4152.6153.8054.98
48.6249.7550.8852.00
42.0243.1544.2645.36
40.4441.5142.5843.64
39.1140.1541.1942.21
36.1237.0838.0338.98
46.4547.5448.6149.68
44.7045.7446.7747.80
43.2344.2445.2446.23
39.9240.8541.7842.70
18.019.020.021.0
22.023.024.025.0
71.7674.7377.6680.55
83.4186.2489.0491.81
66.7869.5472.2774.96
77.6380.2682.8685.44
60.3462.8465.3067.74
70.1472.5274.8777.20
56.1558.4860.7763.04
65.2867.4969.6871.84
53.1155.3157.4759.62
61.7363.8365.9067.95
50.7452.8454.9156.96
58.9860.9862.9664.92
48.8250.8452.8454.81
56.7558.6860.5862.46
54.8956.7558.5960.41
47.2249.1751.1053.01
43.6145.4147.1948.95
50.6952.4154.1155.79
d k = 75 k = 100 k = 150 k = 200 k = 250 k = 300 k = 350 k = 400 k = 550
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
0 1 2 3 4 50.80
0.85
0.90
0.95
1.00
1.05
1.10EFFECT OF E ON
E F
AC
TO
R
0.00 0.05 0.10 0.15 0.20 0.250.995
1.000
1.005
1.010
1.015EFFECT OF
FA
CT
OR
, POISSON’S RATIO
E, YOUNG’S MODULUS (10 psi)
ON
VALUESL
VALUESL
BOTH CURVES ON THIS PAGE ARE USED TO ADJUST THEOF RADIUS OF RELATIVE STIFFNESS ( ) TABLE.L
L VALUESNOTE:
L_AC_070800_1_0050101_01_00
Radius of Relative Stiffness (Effect E and µ on ”L” values)FIGURE-07-08-00-991-005-A01
07-08-00Page 9
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
07-09-00 ACN/PCN Reporting System
**ON A/C A380-800
ACN/PCN Reporting System - Flexible and Rigid Pavements
1. This section gives data about the Aircraft Classification Number (ACN) for an aircraft gross weight inrelation with a subgrade strength value for flexible and rigid pavement.The flexible and rigid pavement requirement graphs are given at standard tire pressure for the weightvariants producing (at the MRW and max aft CG) the lowest MLG load and the highest MLG loadfor each type of aircraft.To find the ACN of an aircraft on flexible and rigid pavement, you must know the aircraft grossweight and the subgrade strength.
NOTE : An aircraft with an ACN equal to or less than the reported PCN can operate on thatpavement, subject to any limitation on the tire pressure.(Ref: ICAO Aerodrome Design Manual, Part 3, Chapter 1, Second Edition 1983).
Example, see FIGURE 7-9-0-991-002-A (sheet 1), calculation of the ACN for flexible pavement for:- An aircraft with a MRW of 492 000 kg (1 084 675 lb),- An aircraft gross weight of 420 000 kg (925 950 lb),- A medium subgrade strength (code B).The ACN for flexible pavement is 43.
Example, see FIGURE 7-9-0-991-002-A (sheet 2), calculation of the ACN for rigid pavement for:- An aircraft with a MRW of 492 000 kg (1 084 675 lb),- An aircraft gross weight of 420 000 kg (925 950 lb),- A medium subgrade strength (code B).The ACN for rigid pavement is 44.
2. Aircraft Classification Number - ACN tableThe table in FIGURE 7-9-0-991-001-A provides ACN data in tabular format similar to the one usedby ICAO in the ”Aerodrome Design Manual Part 3, Pavements - Edition 1983”. If the ACN for anintermediate weight between MRW and the minimum weight of the aircraft is required, refer to thefigures that follow.
NOTE : The CG in the figure title is the CG used for ACN calculation.
07-09-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
WV000
ALL UPMASS
(kg)
LOAD ONONE MAINGEAR LEG
(%)
TIREPRESSURE
(MPa)
562 00019 (WLG)28.5 (BLG)
300 00019 (WLG)28.5 (BLG)
1.50
5655
ACN FORRIGID PAVEMENT
SUBGRADES−MN/m³
ACN FORFLEXIBLE PAVEMENT
SUBGRADES−CBR
HIGH150
66
68
MEDIUM80
78
88
LOW40
91
110
ULTRAL−LOW20
59
56
15HIGH
64
62
10MEDIUM
7575
6LOW
102
106
3ULTRAL−LOW
27 29
29
34
34
39
422725
29
27
31 40
29 30 40
WEIGHTVARIANT
WV001
512 00019 (WLG)28.5 (BLG)
300 00019 (WLG)28.5 (BLG)
1.40
49
48
5757
6875
79
94
51
49
5654
66
65
90
9226 29
28
33
33
38
422725
28
27
31 40
28 30 40
WV002
571 00018.9 (WLG)
28.3 (BLG)
300 00018.9 (WLG)
28.3 (BLG)
1.50
57
56
67
69
79
89
91
111
5957
64
63
76
76
104107
27 2929
3334
38
422725
2826
31 4028 30 39
WV003
512 00019 (WLG)
28.5 (BLG)
300 00019 (WLG)
28.5 (BLG)
1.40
4948
57
576875
7994
5149
5654
6665
9092
26 2928
3333
38
422725
28
27
31 4028 30 40
WV004
562 00019 (WLG)
28.5 (BLG)
300 00019 (WLG)28.5 (BLG)
1.50
5655
6668
7888
91110
5956
6462
75
75102106
27 2929
3434
39
42
2725
29
27
31 4029 30 40
WV005
562 00019 (WLG)
28.5 (BLG)
300 00019 (WLG)
28.5 (BLG)
1.50
5655
6668
7888
91110
5956
6462
7575
102106
27 29
29
34
34
39
42
2725
29
27
31 40
29 30 40
WV006
575 00018.9 (WLG)
28.3 (BLG)
300 00018.9 (WLG)
28.3 (BLG)
1.50
58
56
67
69
80
90
92
113
6057
65
63
77
77
105
108
27 29
29
33
34
38
422725
28
26
31 40
28 30 39
WV007
492 00019 (WLG)28.5 (BLG)
300 00019 (WLG)28.5 (BLG)
1.40
46
46
5454
64
70
75
89
49
47
53
51
62
61
85
8726 29
28
33
33
38
422725
28
27
31 40
28 30 40
WV008
577 00018.9 (WLG)28.3 (BLG)
300 00018.9 (WLG)28.3 (BLG)
1.50
5856
6870
8091
93113
6058
6564
7777
105108
27 2929
3334
38
422725
2826
31 4028 30 39
WV009
537 00019 (WLG)28.5 (BLG)
300 00019 (WLG)28.5 (BLG)
1.50
5352
6263
7482
85103
55
536058
7070
9699
27 2929
3434
39
42
2725
29
27
31 4029 30 40
L_AC_070900_1_0010101_01_00
Aircraft Classification NumberACN Table
FIGURE-07-09-00-991-001-A01
07-09-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
250
2030405060708090100
110
120
600
700
800
900
1 00
01
100
1 20
0
300
350
400
1 30
0
450
500
550
600
(x 1
000
lb)
TIR
E P
RE
SS
UR
E C
ON
ST
AN
T A
T 1
4 ba
r (2
03 p
si)
1 40
0 x
530
R23
40P
R T
IRE
SS
EE
SE
CT
ION
7−
4−0.
AIRCRAFT CLASSIFICATION NUMBER (ACN)
(x 1
000
kg)
AIR
CR
AF
T G
RO
SS
WE
IGH
T
CH
AP
TE
R 1
. SE
CO
ND
ED
ITIO
N 1
983.
ICA
O A
ER
OD
RO
ME
DE
SIG
N M
AN
UA
L P
AR
T 3
AC
N W
AS
DE
TE
RM
INE
D A
S R
EF
ER
EN
CE
D IN
D −
CB
R
3 (
ULT
RA
LO
W)
SU
BG
RA
DE
ST
RE
NG
TH
C −
CB
R
6 (
LOW
)B
− C
BR
10
(ME
DIU
M)
A −
CB
R 1
5 (H
IGH
)
ALP
HA
FA
CT
OR
= 0
.72
FO
R B
LGA
LPH
A F
AC
TO
R =
0.8
FO
R W
LG
L_AC_070900_1_0020101_01_00
Aircraft Classification NumberFlexible Pavement - WV007, MRW 492 000 kg, CG 43% (Sheet 1 of 2) (Sheet 1 of 2)
FIGURE-07-09-00-991-002-A01
07-09-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
250
2030405060708090100
110
120
600
700
800
900
1 00
01
100
1 20
0
300
350
400
1 30
0
450
500
550
600
(x 1
000
lb)
TIR
E P
RE
SS
UR
E C
ON
ST
AN
T A
T 1
4 ba
r (2
03 p
si)
1 40
0 x
530
R23
40P
R T
IRE
SS
EE
SE
CT
ION
7−
4−0.
(x 1
000
kg)
AIR
CR
AF
T G
RO
SS
WE
IGH
T
CH
AP
TE
R 1
. SE
CO
ND
ED
ITIO
N 1
983.
ICA
O A
ER
OD
RO
ME
DE
SIG
N M
AN
UA
L P
AR
T 3
AC
N W
AS
DE
TE
RM
INE
D A
S R
EF
ER
EN
CE
D IN
D −
k =
20
MN
/m³
(ULT
RA
LO
W)
SU
BG
RA
DE
ST
RE
NG
TH
C −
k =
40
MN
/m³
(LO
W)
B −
k =
80
MN
/m³
(ME
DIU
M)
A −
k =
150
MN
/m³
(HIG
H)
AIRCRAFT CLASSIFICATION NUMBER (ACN)
L_AC_070900_1_0020102_01_00
Aircraft Classification NumberRigid Pavement - WV007, MRW 492 000 kg, CG 43% (Sheet 2 of 2) (Sheet 2 of 2)
FIGURE-07-09-00-991-002-A01
07-09-00Page 4
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
2030405060708090100
110
120
600
700
800
900
1 00
01
100
1 20
01
300
(x 1
000
lb)
TIR
E P
RE
SS
UR
E C
ON
ST
AN
T A
T 1
5 ba
r (2
18 p
si)
1 40
0 x
530
R23
40P
R T
IRE
SS
EE
SE
CT
ION
7−
4−0.
CH
AP
TE
R 1
. SE
CO
ND
ED
ITIO
N 1
983.
ICA
O A
ER
OD
RO
ME
DE
SIG
N M
AN
UA
L P
AR
T 3
AC
N W
AS
DE
TE
RM
INE
D A
S R
EF
ER
EN
CE
D IN
D −
CB
R
3 (
ULT
RA
LO
W)
SU
BG
RA
DE
ST
RE
NG
TH
C −
CB
R
6 (
LOW
)B
− C
BR
10
(ME
DIU
M)
A −
CB
R 1
5 (H
IGH
)
ALP
HA
FA
CT
OR
= 0
.72
FO
R B
LGA
LPH
A F
AC
TO
R =
0.8
FO
R W
LG
250
300
350
400
450
500
550
600
(x 1
000
kg)
AIR
CR
AF
T G
RO
SS
WE
IGH
T
AIRCRAFT CLASSIFICATION NUMBER (ACN)
L_AC_070900_1_0030101_01_00
Aircraft Classification NumberFlexible Pavement - WV008, MRW 577 000 kg, CG 41% (Sheet 1 of 2) (Sheet 1 of 2)
FIGURE-07-09-00-991-003-A01
07-09-00Page 5
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
250
2030405060708090100
110
120
600
700
800
900
1 00
01
100
1 20
0
300
350
400
1 30
0
450
500
550
600
(x 1
000
lb)
TIR
E P
RE
SS
UR
E C
ON
ST
AN
T A
T 1
5 ba
r (2
18 p
si)
1 40
0 x
530
R23
40P
R T
IRE
SS
EE
SE
CT
ION
7−
4−0.
(x 1
000
kg)
AIR
CR
AF
T G
RO
SS
WE
IGH
T
CH
AP
TE
R 1
. SE
CO
ND
ED
ITIO
N 1
983.
ICA
O A
ER
OD
RO
ME
DE
SIG
N M
AN
UA
L P
AR
T 3
AC
N W
AS
DE
TE
RM
INE
D A
S R
EF
ER
EN
CE
D IN
D −
k =
20
MN
/m³
(ULT
RA
LO
W)
SU
BG
RA
DE
ST
RE
NG
TH
C −
k =
40
MN
/m³
(LO
W)
B −
k =
80
MN
/m³
(ME
DIU
M)
A −
k =
150
MN
/m³
(HIG
H)
AIRCRAFT CLASSIFICATION NUMBER (ACN)
L_AC_070900_1_0030102_01_00
Aircraft Classification NumberRigid Pavement - WV008, MRW 577 000 kg, CG 41% (Sheet 2 of 2) (Sheet 2 of 2)
FIGURE-07-09-00-991-003-A01
07-09-00Page 6
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
SCALED DRAWINGS
08-00-00 SCALED DRAWINGS
**ON A/C A380-800
Scaled Drawings
1. This section provides the scaled drawings.
NOTE : When printing this drawing, make sure to adjust for proper scaling.
08-00-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
DB1A
0 10 20 30 40 50 60FEET
0 4 8 12 16 20METERS
010
2030
4050
60F
EE
T
04
812
1620
ME
TE
RS
NOTE: WHEN PRINTING THIS DRAWING, MAKE SURE TO ADJUST FOR PROPER SCALING.
L_AC_080000_1_0010101_01_01
Scaled DrawingFIGURE-08-00-00-991-001-A01
08-00-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
AIRCRAFT RESCUE AND FIRE FIGHTING
10-00-00 AIRCRAFT RESCUE AND FIRE FIGHTING
**ON A/C A380-800
Aircraft Rescue and Fire Fighting
1. Aircraft Rescue and Fire Fighting ChartsThis section gives data related to aircraft rescue and fire fighting.The figures contained in this section are the figures that are in the Aircraft Rescue and Fire FightingCharts poster available on AIRBUSWorld and the Airbus website.
10-00-00Page 1
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
L_AC_100000_1_0010101_01_01
Front PageFIGURE-10-00-00-991-001-A01
10-00-00Page 2
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
L_AC_100000_1_0020101_01_02
Highly Flammable and Hazardous Materials and ComponentsFIGURE-10-00-00-991-002-A01
10-00-00Page 3
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING
**ON A/C A380-800
FR
17F
R21
FR
86F
R91
AC
CE
SS
VIA
AC
CE
SS
DO
OR
131
CF
Z
AC
CE
SS
DO
OR
811
VIA
FW
D C
AR
GO
DO
OR
AC
CE
SS
DO
OR
132
CF
ZV
IA F
WD
CA
RG
O D
OO
RB
AT
−2
FR
5
AC
B
A
BC
AC
CE
SS
DO
OR
272
AF
ZV
IA U
PP
ER
DE
CK
BA
T−
1
BA
T−
ES
S
BA
T−
AP
UA
CC
ES
S V
IA B
ULK
CA
RG
O D
OO
R 8
23
DIV
IDE
R N
ET
AC
CE
SS
VIA
AF
T C
AR
GO
DO
OR
L_AC_100000_1_0170101_01_00
Batteries Location and AccessFIGURE-10-00-00-991-017-A01
10-00-00Page 4
Dec 01/13
@A380AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING